阅读说明：本技术 一种无人机弹射装置 (Unmanned aerial vehicle jettison device ) 是由 章继峰 郝天会 宋权威 赵争兵 于 2021-09-24 设计创作，主要内容包括：本发明公开了一种无人机弹射装置,包括挂架、弹射机构、气缸、挡块和气缸支架,所述挂架由加强翼肋向下延伸构成,无人机通过挂架上的挂载销挂载到弹射支架上,弹射支架铰接在弹射机构底座上,同侧的弹射支架通过连杆铰接,与底座构成平行四边形连杆机构,弹射支架上设置有锁杆,锁杆上装有复位弹簧和手动复位杆,锁杆通过复位弹簧抵在底座的限位块上,弹射机构整体通过底座固定在气缸顶面的气缸滑块上,气缸一端的顶面上装有挡块,气缸两端底面安装的气缸支架可收起后向内侧折叠。本发明降低了无人机对起降条件的要求,在无人机脱离弹射架前,将弹射机构的动能转化为一个额外的加速度给无人机加速,减小了弹射机构对气缸的冲击。(The invention discloses an unmanned aerial vehicle ejection device which comprises a hanging frame, an ejection mechanism, a cylinder, a stop block and a cylinder support, wherein the hanging frame is formed by downwards extending a reinforcing wing rib, an unmanned aerial vehicle is hung on the ejection support through a hanging pin on the hanging frame, the ejection support is hinged on a base of the ejection mechanism, the ejection support at the same side is hinged through a connecting rod and forms a parallelogram connecting rod mechanism with the base, a lock rod is arranged on the ejection support, a return spring and a manual return rod are arranged on the lock rod, the lock rod abuts against a limiting block of the base through the return spring, the ejection mechanism is integrally fixed on a cylinder sliding block on the top surface of the cylinder through the base, the stop block is arranged on the top surface of one end of the cylinder, and the cylinder supports arranged on the bottom surfaces of two ends of the cylinder can be folded towards the inner side after being folded. The invention reduces the requirement of the unmanned aerial vehicle on the taking-off and landing conditions, converts the kinetic energy of the ejection mechanism into an additional acceleration to accelerate the unmanned aerial vehicle before the unmanned aerial vehicle is separated from the ejection rack, and reduces the impact of the ejection mechanism on the cylinder.)

1. An unmanned aerial vehicle jettison device which characterized in that: including stores pylon (2), ejection mechanism (6), cylinder (5), dog (4) and cylinder support (8), stores pylon (2) comprises the enhancement rib downwardly extending who is close to wing root department, and unmanned aerial vehicle (1) carries on ejection support (67) through carry round pin (3) on stores pylon (2), and ejection support (67) are connected on base (66) of ejection mechanism (6), and ejection mechanism (6) are whole to be fixed in cylinder slider (7) through base (66), and cylinder slider (7) are located cylinder (5) top surface, are equipped with dog (4) on the top surface of cylinder (5) one end, are fixed with support (8) on the bottom surface at cylinder (5) both ends respectively.

2. The apparatus of claim 1, wherein:

the two sides of the machine body are respectively provided with a hanging rack (2) which is symmetrically distributed along the center line of the machine body, the distance extending from the front end of the hanging rack (2) to the rear end is large, and the front end and the rear end of the hanging rack (2) are respectively provided with a hanging pin (3) which is vertical to the plane of the hanging rack (2).

3. The apparatus of claim 1, wherein:

the base (66) of the ejection mechanism (6) is fixed on the cylinder slide block (7), four ejection brackets (67) which are symmetrically distributed are hinged on the base, and two ejection brackets (67) positioned in front are shorter than two ejection brackets positioned behind.

4. The apparatus of claim 1, wherein:

the distance from the mounting pin (3) to the hinge point of the ejection support (67) is greater than the distance from the impact surface (65) to the hinge point.

5. A method as recited in claim 1, wherein:

the ejection supports (67) on the same side are hinged through connecting rods (68), and the base (66), the connecting rods (68) and the ejection supports (67) form a parallelogram connecting rod mechanism through four hinged points.

6. A method as recited in claim 1, wherein:

the ejection support (67) is provided with a lock rod (61), the lock rod (61) is provided with a return spring (62) and a manual return rod (63), and the lock rod (61) is abutted against a limit block (64) of the base (66) through the return spring (62).

7. A method as recited in claim 1, wherein:

the cylinder support (8) can be folded inwards after being folded, and is arranged at the lower end of the cylinder (5) to be parallel to the cylinder (5).

Technical Field

The invention relates to an unmanned aerial vehicle ejection device, in particular to an unmanned aerial vehicle ejection device driven by compressed air, and belongs to the technical field of unmanned aerial vehicles.

Background

With the increasing maturity of unmanned aerial vehicle technology, the unmanned aerial vehicle is widely applied in various fields, and the unmanned aerial vehicle plays an extremely important role in military and civil fields, and the multi-rotor unmanned aerial vehicle is applied to various different scenes due to the convenience of taking off and landing, but has certain problems in the aspects of dead time, flight speed, load capacity and the like, and the fixed-wing unmanned aerial vehicle can well avoid the problems and has better economy, but has higher requirements on the field when taking off, cannot play a role in scenes without taking off conditions (such as emergency rescue, quick reconnaissance, aerial surveying and mapping and the like), and severely limits the application of the multi-rotor unmanned aerial vehicle in the wider fields.

The utility model provides an effective method that can make unmanned aerial vehicle take off under complicated ground condition, it is harsh to the place of taking off to solve fixed wing unmanned aerial vehicle, unmanned aerial vehicle catapult can roughly be divided into rubber band ejection, motor ejection, rocket boosting, hydraulic pressure ejection and atmospheric pressure ejection several kinds, wherein the atmospheric pressure is launched owing to have simple structure, bearing capacity is strong and reaction rate advantage such as fast, great application prospect has, and improve its launch initial velocity and reduce the key technology that cylinder body impact launched as the atmospheric pressure, be the important factor that restricts atmospheric pressure and launch development and application.

Disclosure of Invention

The invention aims to provide an unmanned aerial vehicle ejection device, which reduces the requirements of an unmanned aerial vehicle on take-off and landing conditions, converts the kinetic energy of an ejection mechanism into an extra acceleration to accelerate the unmanned aerial vehicle before the unmanned aerial vehicle is separated from an ejection frame, and reduces the impact load of the ejection mechanism on a cylinder.

In order to achieve the purpose, the invention is realized by the following technical scheme:

an unmanned aerial vehicle jettison device which characterized in that: the unmanned aerial vehicle catapult comprises a hanging frame, a catapult mechanism, an air cylinder, a stop block and an air cylinder support, wherein the hanging frame is formed by downwards extending a reinforced wing rib close to a wing root;

furthermore, two sides of the machine body are respectively provided with a hanging frame which is symmetrically distributed along the center line of the machine body, the distance extending from the front end to the rear end of each hanging frame is large, and the front end and the rear end of each hanging frame are respectively provided with a hanging pin;

furthermore, the ejection mechanism base is fixed on the cylinder sliding block, four ejection supports which are symmetrically distributed are hinged on the ejection mechanism base, and two ejection supports positioned in front are shorter than two ejection supports positioned behind;

further, the distance from the mounting pin to the hinge point of the ejection support and the base is greater than the distance from the impact surface to the hinge point;

furthermore, the ejection supports on the same side are hinged through a connecting rod, and the base, the connecting rod and the ejection supports form a parallelogram connecting rod mechanism through four hinged points;

furthermore, a lock rod is arranged on the ejection support, a return spring and a manual return rod are arranged on the lock rod, and the lock rod is abutted against a limiting block of the base through the return spring;

furthermore, the cylinder support can be folded inwards after being folded, and the lower end of the cylinder is arranged in parallel with the cylinder.

The invention has the beneficial effects that:

(1) the ejection support is hinged on the base, and before the unmanned aerial vehicle is separated from the ejection support, the kinetic energy of the ejection mechanism is converted into the kinetic energy of the unmanned aerial vehicle, so that the initial ejection speed is improved, and the impact of the ejection mechanism on the cylinder is reduced;

(2) the ejection supports on the same side are hinged through the connecting rods and form a parallelogram connecting rod mechanism with the base, so that the unmanned aerial vehicle is always kept parallel to the air cylinder in the ejection process;

(3) the ejection mechanism is provided with an automatic unlocking lock rod, and the unmanned aerial vehicle can be ensured to be separated from the ejection frame and automatically unlocked by the instant lock rod in the process of ensuring the stability of the unmanned aerial vehicle in the ejection process.

(4) The cylinder support can be folded inwards after being folded, so that the portability and the flexibility are improved;

drawings

FIG. 1 is a schematic side view of an embodiment;

FIG. 2 is a schematic perspective view of an embodiment of an unmanned aerial vehicle and a pylon;

FIG. 3 is a schematic view of a three-dimensional half-section of an ejection mechanism according to an embodiment;

in the figure, 1-unmanned plane; 2-hanging rack; 3-mounting a pin; 4-a stop block; 5-air cylinder; 6-ejection mechanism; 61-locking bar; 62-a return spring; 63-a manual reset lever; 64-a limiting block; 65-impact surface; 66-a base; 67-a launch cradle; 68-a connecting rod; 7-cylinder slide block; 8-cylinder support.

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 embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative efforts based on the embodiments of the present invention belong to the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus should not be construed as limiting the scope of the present invention.

Referring to fig. 1, fig. 2 and fig. 3, the present embodiment provides an unmanned aerial vehicle ejection device, which is characterized in that: including stores pylon 2, ejection mechanism 6, cylinder 5, dog 4 and cylinder support 8, stores pylon 2 comprises the enhancement rib downwardly extending who is close to wing root department, and unmanned aerial vehicle 1 carries on ejection support 67 through carry pin 3 on the stores pylon 2, and ejection support 67 is connected on ejection mechanism 6's base 66, and ejection mechanism 6 is whole to be fixed in cylinder slider 7 through base 66, and cylinder slider 7 is located the 5 top surfaces of cylinder, is equipped with dog 4 on the top surface of 5 one ends of cylinder, is fixed with support 8 on the bottom surface at 5 both ends of cylinder respectively.

Referring to fig. 1, the central portion of the base 66 of the ejection mechanism 6 is fixed on the cylinder slider 7 by bolts, and four symmetrically distributed ejection brackets 67 are hinged on the base, and the positions of the ejection brackets correspond to the four mounting pins 3 on the unmanned aerial vehicle 1, so that the mounting pins 3 at the rear end of the hanging rack 2 do not impact the front ejection bracket 67, and the unmanned aerial vehicle 1 is parallel to the cylinders, and the two ejection brackets 67 at the front are shorter than the two at the rear, that is, the heights of the two ejection brackets 67 at the front and the hanging rack 2 are the same as the two at the rear.

Referring to fig. 1, after the three legs of the cylinder frame 8 are folded inward, the front and rear cylinder frames 8 may be folded inward to be disposed at the lower end of the cylinder 5 in parallel with the cylinder 5.

Referring to fig. 2, fuselage both sides are close to wing root department and respectively have a stores pylon 2 to along fuselage central line symmetric distribution, both ends all are equipped with perpendicular to stores pylon 2 plane to the convex mount pin 3 in both sides around the stores pylon 2, and the distance that the more rear end of stores pylon 2 front ends extends is big, prevents that unmanned aerial vehicle 1 when breaking away from ejection support 67, and the mount pin 3 striking of stores pylon 2 rear end is to preceding ejection support 67.

Referring to fig. 3, the distance from the mounting pin 3 to the hinge point between the ejection bracket 67 and the base 66 is greater than the distance from the impact surface 65 to the hinge point, so that the ejection bracket forms a lever with respect to the hinge point, the impact load during impact is converted into an additional force for accelerating the unmanned aerial vehicle 1, the ejection bracket 67 on the same side is hinged by the connecting rod 68, the base 66, the connecting rod 68 and the ejection bracket 67 form a parallelogram link mechanism by four hinge points, so that the unmanned aerial vehicle 1 always keeps parallel to the cylinder 5 when the ejection bracket 67 rotates along the hinge point,

referring to fig. 3, be provided with the locking lever 61 that can follow ejection support 67 length direction gliding on the ejection support 67, the cover has reset spring 62 and manual release lever 63 on the locking lever 61, locking lever 61 locking lever is through propping on the stopper 64 of base 66 in the latched position, offset the power that reset spring 62 opened the locking lever, along with the ejection support rotates the position that unmanned aerial vehicle breaks away from, the locking lever bottom breaks away from the stopper 64 of base 66, at this moment, spring down the locking lever to the unlocked position, at the unlocked position through lifting manual release lever 63, rotatory ejection support 67 is to the position before launching simultaneously, the locking lever bottom is propped on the stopper 64 of base 66 again, thereby realize the locking.

The use method of the invention is as follows with the attached drawings:

1) opening the cylinder support 8, placing the cylinder support in a locking position, adjusting the height of each telescopic leg of the cylinder support 8 until the inclination angle of the cylinder 5 is the same as the preset takeoff attack angle, and communicating an air source for the cylinder 5;

2) the ejection mechanism locking rod 61 is opened through the manual reset rod 63, the mounting pin 3 is placed in a fixing groove of the ejection bracket 67, the locking rod 61 is manually locked, and the ejection mechanism 6 is pulled backwards to an ejection position;

3) checking each control surface and an engine of the unmanned aerial vehicle 1, placing an engine throttle at a full-power position after determining to be normal, switching on an air source valve of an air cylinder 5, and driving an ejection mechanism 6 and the unmanned aerial vehicle 1 to slide in an accelerated manner by an air cylinder slide block 7;

4) when ejection mechanism 6 and unmanned aerial vehicle 1 slided to dog 4 positions, striking face 65 collision dog 4, ejection support 67 takes place to rotate, locking lever 61 makes locking lever 61 slide down to unblank automatically under reset spring 62 and stopper 64's effect, because striking face 65 and carry the distance difference of round pin 3 and ejection support 67 pivot department, carry round pin 3 department and can produce an extra acceleration and give unmanned aerial vehicle 1 with higher speed, and ejection mechanism 6 can slow down and stop, unmanned aerial vehicle 1 breaks away from the ejection rack and takes off.

The above embodiments are merely illustrative of the technical ideas and features of the present invention, and the purpose thereof is to enable those skilled in the art to understand the contents of the present invention and implement the present invention, and not to limit the protection scope of the present invention. All equivalent changes and modifications made according to the spirit of the present invention should be covered within the protection scope of the present invention.