CN212709950U - Undercarriage damping device of fixed wing gasoline power unmanned aerial vehicle - Google Patents
Undercarriage damping device of fixed wing gasoline power unmanned aerial vehicle Download PDFInfo
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- CN212709950U CN212709950U CN202022089717.1U CN202022089717U CN212709950U CN 212709950 U CN212709950 U CN 212709950U CN 202022089717 U CN202022089717 U CN 202022089717U CN 212709950 U CN212709950 U CN 212709950U
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Abstract
The utility model relates to a landing gear damping device of a fixed wing gasoline power unmanned aerial vehicle, which comprises a tire, a fixed plate, a pair of support rods, a large spiral spring and a small spiral spring, wherein the fixed plate is arranged at the bottom of the body of the unmanned aerial vehicle; big coil spring and little coil spring are a pair of, and big coil spring and little coil spring are X shape and distribute, and the centre is connected through the ring, and big coil spring is located the below, and its one end is connected with the ring, and the other end is connected with the bracing piece tip, and little coil spring is located the top, and one end is connected with the ring, and the other end is connected with the fixed plate. The utility model discloses a fixed wing unmanned aerial vehicle damping device, coil spring and ring play absorbing effect, can disperse when fixed wing unmanned aerial vehicle descends fast with the collision impact force on ground, ensure that unmanned aerial vehicle descending process is steady, unmanned aerial vehicle each side structural performance is not influenced.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle accessory technical field, concretely relates to fixed wing gasoline power unmanned aerial vehicle undercarriage damping device.
Background
Unmanned aerial vehicle is called for short for unmanned aerial vehicle, be the unmanned aerial vehicle who utilizes radio remote control equipment and self-contained program control device to control, unmanned aerial vehicle is unmanned aerial vehicle's the general name in fact, classify according to the flight platform configuration, unmanned aerial vehicle can divide into fixed wing unmanned aerial vehicle, rotor unmanned aerial vehicle, unmanned airship, umbrella wing unmanned aerial vehicle, flapping wing unmanned aerial vehicle etc. compare with manned aircraft, it has small, the cost is low, high durability and convenient use, low to operational environment requirement, advantages such as battlefield viability is stronger. Since the unmanned aircraft has important significance for future air battles, the research and development work of the unmanned aircraft is carried out in all major military countries in the world. In addition, the unmanned aerial vehicle has wide application and has better development prospect in the industries of police, city management, agriculture, geology, meteorology, electric power, emergency rescue and disaster relief, video shooting and the like.
The landing gear is the important component of unmanned aerial vehicle, is used for supporting aircraft gravity when parking on the ground, slides, takes off and lands and the roll off, bears the device of corresponding load, and unmanned aerial vehicle is when descending, and the landing gear is first to descend, and it can consume and absorb the impact energy of aircraft when landing. Wherein fixed wing petrol power unmanned aerial vehicle has that flight speed is fast, and flying height is high, advantages such as hang-time is long, and the speed when descending is great, therefore the impact energy of ground to the undercarriage is very big. But the big shock attenuation effect of unmanned aerial vehicle undercarriage on the present market is not good, can't effectively alleviate the collision impact force of unmanned aerial vehicle and ground, and unstable when leading to unmanned aerial vehicle to descend receives great impact easily, and the inside comparatively accurate instrument, the equipment that need be equipped with of unmanned aerial vehicle usually, and stronger impact will be to the accuracy that reduces instrument and equipment, and the structural performance of each part of unmanned aerial vehicle consequently receives the influence.
SUMMERY OF THE UTILITY MODEL
Not enough more than, the utility model provides a fixed wing petrol power unmanned aerial vehicle undercarriage damping device can effectively reduce when unmanned aerial vehicle descends with the collision energy on ground, and guarantee unmanned aerial vehicle descends steadily, and each aspect structural performance is not influenced.
The technical scheme of the utility model is that:
a landing gear damping device of a fixed wing gasoline power unmanned aerial vehicle comprises tires, a fixing plate, a pair of supporting rods, a large spiral spring and a small spiral spring, wherein the fixing plate is installed at the bottom of the body of the unmanned aerial vehicle; big coil spring and little coil spring are a pair of, and big coil spring and little coil spring are X shape and distribute, and the centre is connected through the ring, big coil spring is located the below, and its one end is connected with the ring, and the other end is connected with the bracing piece tip, little coil spring is located the top, and one end is connected with the ring, and the other end is connected with the fixed plate.
The large spiral spring and the small spiral spring are damping springs.
The large spiral spring is fixedly connected with the supporting rod through a first bolt and a first nut.
The small spiral spring is fixedly connected with the fixed plate through a lifting ring screw and a lifting ring nut.
The support rod is fixedly connected with the tire through a bolt and a nut II.
The utility model discloses an undercarriage damping device includes fixed plate, bracing piece, coil spring and ring, and coil spring is including a pair of big coil spring that is located the below and a pair of little coil spring that is located the top, and two pairs of coil springs are X-shaped and distribute, and one end is connected with fixed plate and bracing piece fixed connection respectively, and one end is connected with the ring respectively in addition, coil spring is damping spring, and the bracing piece is held to big coil spring's one end, and the other end supports the ring, and little coil spring's one end supports the fixed plate, and the ring is held to the other end, and two pairs of coil spring's the other end is connected with the ring through the overhead kick.
When fixed wing petrol unmanned aerial vehicle landed, because speed is very fast, the fuselage is heavier, pass through bracing piece and fixed plate with the energy that ground collision produced and reach coil spring, the little coil spring atress of top is tensile, can absorb some impact energy, the big coil spring atress compression of below, also can absorb some impact energy, and dissipate energy transfer middle ring, produce the reaction force simultaneously, the impact force that receives when further slowing down fixed wing unmanned aerial vehicle landing, reach absorbing effect with this, ensure that fixed wing unmanned aerial vehicle's decline process is more stable.
Drawings
Fig. 1 is a front view of a landing gear damping device of a fixed wing gasoline powered unmanned aerial vehicle of the present invention;
fig. 2 is a partially enlarged view of the coil spring device.
Detailed Description
The conception, the specific structure and the technical effects of the present invention will be further described with reference to the accompanying drawings, so as to fully understand the objects, the features and the effects of the present invention.
Referring to fig. 1 and 2, the utility model discloses a fixed wing petrol power unmanned aerial vehicle undercarriage damping device, unmanned aerial vehicle are equipped with fuselage 14, wing 1 and screw 13, and screw 13 fixes on fuselage 14 through stationary cylinder 15. Unmanned aerial vehicle undercarriage damping device, including tire 3, fixed plate 12, bracing piece 2, big coil spring 6 and little coil spring 9, fixed plate 12 is installed in 14 bottoms of unmanned aerial vehicle fuselage, and bracing piece 2 is a pair of, 2 one ends of bracing piece and fixed plate 12 fixed connection, and the other end passes through bolt 5 and two 4 and 3 fixed connection of tire of nut. Big coil spring 6 and little coil spring 9 are a pair of, and big coil spring 6 and little coil spring 9 are vertical X shape and distribute, connect through ring 7 in the middle of, and big coil spring 6 is located the below, and its one end is connected with ring 7, and the other end passes through bolt 5 and nut 8 and 2 end fixed connection of bracing piece, and little coil spring 9 is located the top, and one end is connected with ring 7, and the other end passes through eyebolt 10 and eyenut 11 and fixed plate 12 fixed connection. Two pairs of helical springs are damping springs, and one end of each helical spring is connected with the circular ring 7 through an inverted hook.
The utility model discloses a when fixed wing petrol unmanned aerial vehicle landed, because speed is very fast, the fuselage is heavier, pass to coil spring through bracing piece 2 and fixed plate 12 with the energy that ground collision produced, the little coil spring 9 atress of top is tensile, can absorb some impact energy, the big coil spring 6 atress compression in below, also can absorb some impact energy, and dissipate middle ring 7 with energy transfer, produce the reaction force simultaneously, the impact force that receives when further slowing down fixed wing unmanned aerial vehicle landed, reach absorbing effect with this, the impact that makes unmanned aerial vehicle receive is littleer, coil spring is damping spring and be "X type" and distribute, dual damping design can ensure that fixed wing unmanned aerial vehicle's decline process is more stable.
The above disclosure is only for the embodiment of the present invention, however, the present invention is not limited thereto, and any changes that can be considered by those skilled in the art should fall within the protection scope of the present invention.
Claims (5)
1. The landing gear damping device of the fixed wing gasoline power unmanned aerial vehicle is characterized by comprising a tire (3), a fixing plate (12), a supporting rod (2), a large spiral spring (6) and a small spiral spring (9), wherein the fixing plate (12) is installed at the bottom of a body (14) of the unmanned aerial vehicle, the supporting rods (2) are in a pair, one end of each supporting rod (2) is fixedly connected with the fixing plate (12), and the other end of each supporting rod is connected with the tire (3); big coil spring (6) and little coil spring (9) are a pair of, and big coil spring (6) and little coil spring (9) are X-shaped and distribute, and the centre is connected through ring (7), big coil spring (6) are located the below, and its one end is connected with ring (7), and the other end is connected with bracing piece (2) tip, little coil spring (9) are located the top, and one end is connected with ring (7), and the other end is connected with fixed plate (12).
2. The landing gear damping device for fixed wing gasoline powered unmanned aerial vehicle according to claim 1, wherein the large coil spring (6) and the small coil spring (9) are damping springs.
3. The landing gear damping device for the fixed wing gasoline powered unmanned aerial vehicle according to claim 1, wherein the large coil spring (6) is fixedly connected with the support rod (2) through a bolt (5) and a first nut (8).
4. The landing gear damping device for the fixed wing gasoline powered unmanned aerial vehicle according to claim 1, wherein the small coil spring (9) is fixedly connected with the fixing plate (12) through a lifting eye screw (10) and a lifting eye nut (11).
5. The landing gear damping device for the fixed-wing gasoline-powered unmanned aerial vehicle according to claim 1, wherein the support rod (2) is fixedly connected with the tire (3) through a bolt (5) and a nut II (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022089717.1U CN212709950U (en) | 2020-09-22 | 2020-09-22 | Undercarriage damping device of fixed wing gasoline power unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022089717.1U CN212709950U (en) | 2020-09-22 | 2020-09-22 | Undercarriage damping device of fixed wing gasoline power unmanned aerial vehicle |
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| CN212709950U true CN212709950U (en) | 2021-03-16 |
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| CN202022089717.1U Active CN212709950U (en) | 2020-09-22 | 2020-09-22 | Undercarriage damping device of fixed wing gasoline power unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113190023A (en) * | 2021-03-31 | 2021-07-30 | 成都飞机工业（集团）有限责任公司 | Control method for full-autonomous arresting landing of carrier-borne unmanned aerial vehicle |
-
2020
- 2020-09-22 CN CN202022089717.1U patent/CN212709950U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113190023A (en) * | 2021-03-31 | 2021-07-30 | 成都飞机工业（集团）有限责任公司 | Control method for full-autonomous arresting landing of carrier-borne unmanned aerial vehicle |
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