CN218400953U

CN218400953U - Aircraft capable of buffering landing

Info

Publication number: CN218400953U
Application number: CN202221111589.9U
Authority: CN
Inventors: 胡华伟; 杨帆
Original assignee: Hunan Huifei Intelligent Technology Co ltd
Current assignee: Hunan Huifei Intelligent Technology Co ltd
Priority date: 2022-05-10
Filing date: 2022-05-10
Publication date: 2023-01-31
Anticipated expiration: 2032-05-10

Abstract

The utility model discloses a can cushion aircraft that descends relates to aircraft technical field, which comprises a housing, the four corners of casing is all rotated and is provided with the exhibition arm, the end rigidity of exhibition arm is provided with the motor, the fixed cover of spindle of motor is equipped with the rotating vane, the bottom surface of casing is provided with supporting mechanism along fixed outward. This equipment is through setting up crown plate and caulking groove, when equipment flies off ground, through the extension of pressure spring, makes the stabilizer blade draw in whole supporting mechanism and gathers a bundle and become the toper structure, reduces the windage, and the response is controlled in the lifting means flight instantaneity, and the stabilizer blade is concentrated to equipment focus bottom side, and leveling operation when the equipment of being convenient for more flies, when descending, the foot pad that falls shifts up at first realizes the buffering, and the foot pad that falls conflicts triggers when the ring shifts up, realizes the quick expansion of stabilizer blade. When the device falls to the ground, the gravity center of the device is firstly determined and supported, so that the stable falling of the device is facilitated, and the buffering effect is more reliable.

Description

Aircraft capable of buffering landing

Technical Field

The utility model relates to an aircraft technical field specifically is an aircraft that can cushion and descend.

Background

The small remote control aircraft greatly facilitates monitoring and surveying of terrain environment and image acquisition of entertainment activities.

The prior patent (publication number: CN 215752987U) discloses an aircraft with a landing buffer protection structure, which comprises a controller assembly, a support arm, a motor, blades and a buffer undercarriage, wherein the buffer undercarriage is arranged, four movable supporting legs are arranged at the corners of the buffer undercarriage, the movable supporting legs adopt a telescopic structure, the top ends of movable tubes of the movable supporting legs rotate through a fixed rotating shaft, a supporting structure is arranged, and a movable ring of the supporting structure is supported through a spring.

The inventor finds that the following problems exist in the prior art:

1. when the device flies, the supporting structure is always kept in an unfolded state, the framework space is large when the device is unfolded, and the wind resistance of the unfolded supporting structure is large in the flying process of equipment, so that the instantaneity of the steering and shifting operation response of the equipment is influenced;

2. when the device is flying, the weight of the unfolded supporting structure is shared to four corners of the equipment, and the stressed bottom cushion and the connecting rod are in an active state, so that the equipment is easily influenced by self inertia when moving, is easy to shake, influences the gravity center position of the equipment, and is not beneficial to leveling and position keeping when flying.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a can cushion aircraft that descends to when solving aircraft flight among the above-mentioned background art, the bearing structure of expansion influences the instant response that equipment flight removed and controls, influences the leveling of equipment position and the problem that keeps.

In order to achieve the above purpose, the utility model discloses a following technical scheme realizes: the utility model provides an aircraft that can cushion and descend, includes the casing, the four corners of casing all rotates and is provided with the exhibition arm, the end rigidity of exhibition arm is provided with the motor, the fixed cover of spindle of motor is equipped with the vane, the bottom surface of casing is provided with supporting mechanism along fixed outward, the bottom surface central point of casing puts fixed buffer gear that is provided with, supporting mechanism and buffer gear swing joint.

The supporting mechanism comprises a connecting ring, the connecting ring is fixedly arranged on the bottom surface of the casing, the bottom of the connecting ring is rotatably connected with a supporting leg, an embedding groove is formed in the bottom of the supporting leg, a push-pull arm is rotatably connected to the surface of the supporting leg, the push-pull arm is matched with the embedding groove, and a trigger ring is rotatably connected to the bottom of the push-pull arm.

The buffer mechanism comprises a connecting seat, the connecting seat is fixedly arranged at the center of the bottom surface of the casing, a sleeve is fixedly penetrated at the bottom of the connecting seat, a sleeve rod is inserted and sleeved on the inner side of the sleeve, and a pressure spring is sleeved between the top of the sleeve rod and the top surface of the inner wall of the sleeve.

The fixed cover in bottom end position of loop bar is equipped with the callus on the sole that falls, the callus on the sole that falls cooperatees with the bottom that triggers the ring, the fixed coupling in middle part of loop bar has the crown plate, the crown plate cooperatees with the top that triggers the ring.

Optionally, the number of the support legs is four, and the support legs are arranged in an annular array around the circle center of the connecting ring.

Optionally, the length of the push-pull arm is smaller than the length of the caulking groove, and the width of the push-pull arm is smaller than the width of the caulking groove.

Optionally, the connecting seat is arranged at the circle center of the connecting ring, and the connecting seat is in threaded connection with the top end of the sleeve.

Optionally, the bottom of triggering the ring sets up for the conical surface, the lower extreme of loop bar runs through trigger the ring.

Optionally, the crown plate sets up trigger the upside of ring, the callus on the sole setting that falls is in trigger the downside of ring, the bottom surface of crown plate and the top of falling the callus on the sole are provided with the clearance between.

The utility model discloses a technological effect and advantage:

1. the device is provided with the ring plate and the caulking groove, when the device flies up and leaves the ground, the trigger ring can be pushed to move downwards through the extension of the pressure spring, so that the support legs are folded, the push-pull arm is nested into the inner side of the caulking groove, the whole supporting mechanism is bundled into a conical structure, the overhead space occupation is reduced, the wind resistance is reduced, and the instantaneity of the flight control response of the device is improved.

2. When the equipment flies, the equipment is pushed by the annular plate, the support legs are concentrated to the bottom side of the gravity center of the equipment, the weight of the support legs is close to the gravity center, and the leveling operation of the equipment during flying is facilitated.

3. This equipment is when descending, and the foot pad that falls contacts ground at first and drives the loop bar and for the whole pressure spring that shifts up of equipment realizes the buffering, and the foot pad that falls conflicts when triggering the ring and shift up, realizes the quick expansion of stabilizer blade. Because the foot pad that falls is close to the equipment focus, at first confirm when falling to the ground with the bracing piece focus, be favorable to more steadily falling to the ground of equipment, avoid falling to the ground after because each stabilizer blade supports the atress different, equipment slope tip, its buffering falls to the ground the effect more reliable.

Drawings

FIG. 1 is a top view of the structure of the present invention;

fig. 2 is a bottom view of the structure of the present invention;

fig. 3 is a longitudinal development view of the supporting mechanism and the buffering mechanism of the present invention.

In the figure: 1. a housing; 2. stretching the arm; 3. a motor; 4. rotating leaves; 5. a support mechanism; 501. a connecting ring; 502. a support leg; 503. caulking grooves; 504. a push-pull arm; 505. a trigger ring; 6. a buffer mechanism; 601. A connecting seat; 602. a sleeve; 603. a loop bar; 604. a pressure spring; 605. dropping the foot mat; 606. and (7) a ring plate.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.

The utility model provides an aircraft that can cushion and descend as shown in fig. 1-3, including casing 1, casing 1's four corners is all rotated and is provided with exhibition arm 2, and the end rigidity of exhibition arm 2 is provided with motor 3, and motor 3's spindle fixing cover is equipped with rotary vane 4, and casing 1's bottom surface is provided with supporting mechanism 5 along fixed outward, and casing 1's bottom surface central point rigidity is provided with buffer gear 6, supporting mechanism 5 and buffer gear 6 swing joint.

Supporting mechanism 5 includes connecting ring 501, the fixed bottom surface that sets up at casing 1 of connecting ring 501, the bottom of connecting ring 501 is rotated and is connected with stabilizer blade 502, the quantity of stabilizer blade 502 is four, stabilizer blade 502 sets up around the centre of a circle of connecting ring 501 ring array, caulking groove 503 has been seted up to the bottom of stabilizer blade 502, the surface rotation of stabilizer blade 502 is connected with push-and-pull arm 504, push-and-pull arm 504 and caulking groove 503 are mutually supported, the bottom of push-and-pull arm 504 is rotated and is connected with and triggers ring 505, the bottom that triggers ring 505 is the conical surface setting, when equipment falls to the ground, it can overlap and establish as triggering the bottom of ring 505 and drive and trigger ring 505 production and move up the action to fall foot pad 605. The sleeve rod 603 penetrates through the trigger ring 505 and forms a penetrating and sleeving position relationship with the trigger ring 505. By arranging the ring plate 606 and the caulking groove 503, when the equipment flies off the ground, the trigger ring 505 can be pushed to move downwards by extending the pressure spring 604, so that the support legs 502 are folded, and the push-pull arm 504 is nested into the inner side of the caulking groove 503, so that the whole supporting mechanism 5 is bundled into a cone-shaped structure, the overhead space occupation is reduced, the wind resistance is reduced, and the instantaneity of the flight control response of the equipment is improved.

Buffer gear 6 includes connecting seat 601, and the fixed central point that sets up in casing 1 bottom surface of connecting seat 601 puts, and connecting seat 601 sets up the centre of a circle position at connecting ring 501, and connecting seat 601 sets up with the top of sleeve pipe 602 one-tenth threaded connection, and rotatory sleeve pipe 602 can be dismantled sleeve pipe 602 and connecting seat 601, the maintenance of the equipment of being convenient for. A sleeve 602 penetrates through and is fixed at the bottom of the connecting seat 601, a sleeve rod 603 penetrates through and is sleeved on the inner side of the sleeve 602, the sleeve rod 603 is perpendicular to the bottom surface of the casing 1, and when the casing 1 is horizontally placed, the sleeve rod 603 is on a vertical line of the center of gravity of the equipment. A pressure spring 604 is sleeved between the top of the sleeve rod 603 and the top surface of the inner wall of the sleeve 602.

The fixed cover in bottom end position of loop bar 603 is equipped with the callus on the sole 605 that falls, the callus on the sole 605 that falls is the taper structure, the callus on the sole 605 that falls is the rubber material, the inboard parcel that the foot that falls fills up 605 has the metal block of counter weight, the foot that falls fills up 605 and triggers the bottom cooperation of ring 505, the fixed ring plate 606 that has cup jointed in middle part of loop bar 603, ring plate 606 and the top cooperation that triggers ring 505, ring plate 606 and the foot that falls fill up 605 and set up respectively in the upper and lower side that triggers ring 505, it is gapped to remain between the bottom surface of ring plate 606 and the top that the foot that falls filled up 605. When the device flies, the device is pushed by the ring plate 606, the support legs 502 are concentrated to the bottom side of the gravity center of the device, the weight of the support legs 502 is close to the gravity center, and the leveling operation of the device during flying is facilitated.

When the device is descended, the foot-falling pad 605 firstly contacts the ground to drive the loop bar 603 to move upwards relative to the device integrally to realize buffering by the pressure spring 604, and when the foot-falling pad 605 butts against the trigger ring 505 to move upwards, the support foot 502 is unfolded quickly. Because the foot pad 605 that falls is close to the equipment focus, at first confirm with the bracing piece focus when falling to the ground, be favorable to more steadily falling to the ground of equipment, avoid falling to the ground back because each stabilizer blade 502 supports the atress different, the equipment slope is tumbled, and its buffering falls to the ground the effect more reliable.

This practical theory of operation: when the aircraft capable of buffering landing is lifted off the ground during takeoff, the elastic potential energy of the pressure spring 604 is released, the push rod is enabled to move downwards, the push rod drives the ring plate 606 to move downwards and contact the trigger ring 505, the foot drop pad 605 is separated from the trigger ring 505, the ring plate 606 pushes the trigger ring 505 to be far away from the bottom surface of the machine shell 1, the ring plate 606 pulls the push-pull arm 504, the push-pull arm 504 pulls the support foot 502, the support foot 502 is enabled to generate a beam retracting action towards the axis of the connecting ring 501 until the push-pull arm 504 is embedded into the inner side of the caulking groove 503, at the moment, the whole supporting mechanism 5 is in a conical structure, the weight of the support foot 502 is concentrated close to the sleeve rod 603 and the foot drop pad 605 and is concentrated below the center of the bottom surface of the machine shell 1 and is closer to the gravity center of the whole equipment, after the beam retracting, the overhead space between the hardware of the supporting mechanism 5 is small, the wind resistance is reduced, the influence on the equipment flying and the equipment is smaller when the equipment is reversed, and the responsiveness of flying operation and control of the equipment is improved.

When the landing device lands on the ground, the landing pad 605 contacts the ground firstly, the landing pad 605 is close to the bottom surface of the casing 1, the landing pad 605 drives the sleeve rod 603 to move upwards, so that the pressure spring 604 contracts, the pressure spring 604 deforms to provide a buffer for the landing action, the sleeve rod 603 moves upwards to drive the ring plate 606 to be separated from the trigger ring 505, the landing pad 605 collides against the trigger ring 505 to continue moving upwards, the push-pull arm 504 is pushed by the landing pad 605 and the trigger ring 505 to drive the support leg 502 to expand rapidly, and the multipoint supporting effect is achieved.

Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications and variations can be made in the embodiments or in part of the technical features of the embodiments without departing from the spirit and the scope of the invention.

Claims

1. The utility model provides an aircraft that can cushion and descend, includes casing (1), the four corners of casing (1) all rotates and is provided with exhibition arm (2), the end rigidity of exhibition arm (2) is provided with motor (3), the fixed cover of spindle of motor (3) is equipped with rotary vane (4), its characterized in that: a supporting mechanism (5) is fixedly arranged on the outer edge of the bottom surface of the machine shell (1), a buffering mechanism (6) is fixedly arranged at the center position of the bottom surface of the machine shell (1), and the supporting mechanism (5) is movably connected with the buffering mechanism (6);

the supporting mechanism (5) comprises a connecting ring (501), the connecting ring (501) is fixedly arranged on the bottom surface of the machine shell (1), the bottom of the connecting ring (501) is rotatably connected with a supporting leg (502), the bottom of the supporting leg (502) is provided with a caulking groove (503), the surface of the supporting leg (502) is rotatably connected with a push-pull arm (504), the push-pull arm (504) is matched with the caulking groove (503), and the bottom of the push-pull arm (504) is rotatably connected with a trigger ring (505);

the buffer mechanism (6) comprises a connecting seat (601), the connecting seat (601) is fixedly arranged at the center of the bottom surface of the machine shell (1), a sleeve (602) penetrates through and is fixed at the bottom of the connecting seat (601), a sleeve rod (603) is inserted and sleeved on the inner side of the sleeve (602), and a pressure spring (604) is sleeved between the top of the sleeve rod (603) and the top surface of the inner wall of the sleeve (602);

the fixed cover in bottom end position of loop bar (603) is equipped with and falls callus on the sole (605), fall callus on the sole (605) and trigger the bottom of ring (505) and cooperate, the fixed crown plate (606) that has cup jointed in middle part of loop bar (603), crown plate (606) cooperate with the top of triggering ring (505).

2. An aircraft with a cushioned landing according to claim 1, wherein: the number of the supporting feet (502) is four, and the supporting feet (502) are arranged in an annular array around the circle center of the connecting ring (501).

3. An aircraft with cushioned descent in accordance with claim 1, wherein: the length of the push-pull arm (504) is smaller than that of the caulking groove (503), and the width of the push-pull arm (504) is smaller than that of the caulking groove (503).

4. An aircraft with a cushioned landing according to claim 1, wherein: the connecting seat (601) is arranged at the circle center position of the connecting ring (501), and the connecting seat (601) is in threaded connection with the top end of the sleeve (602).

5. An aircraft with cushioned descent in accordance with claim 4, wherein: the bottom of trigger ring (505) is the conical surface setting, the lower extreme of loop bar (603) runs through trigger ring (505).

6. An aircraft with a cushioned landing according to claim 5, wherein: the ring plate (606) is arranged on the upper side of the trigger ring (505), the foot falling pad (605) is arranged on the lower side of the trigger ring (505), and a gap is formed between the bottom surface of the ring plate (606) and the top of the foot falling pad (605).