CN111532421A - A take-off and landing device for ultralight small-size unmanned vehicles - Google Patents
A take-off and landing device for ultralight small-size unmanned vehicles Download PDFInfo
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- CN111532421A CN111532421A CN202010491570.0A CN202010491570A CN111532421A CN 111532421 A CN111532421 A CN 111532421A CN 202010491570 A CN202010491570 A CN 202010491570A CN 111532421 A CN111532421 A CN 111532421A
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- fixing piece
- vertical tail
- skid plate
- landing
- clamping grooves
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides a take-off and landing device for an ultra-light small-sized unmanned aerial vehicle, which consists of a skid plate, a vertical tail fixing piece and a pulley mechanism; according to the size and position of the vertical tail of the airplane, two pairs of vertical tail fixing piece clamping grooves with 4 positions and 2 prescription-shaped tire limiting holes are respectively formed in the skid plate. Two vertical tail fixing frames penetrate through the clamping grooves to be fixedly connected with the airplane vertical tail; 2 the prescription tire limit hole is the limit mounting hole corresponding to the corresponding vehicle-mounted fixing device position, so that the undercarriage can not only automatically slide off and land, but also adopt vehicle-mounted take-off and slide off and land when the runway environment is poor. The landing gear has good compression resistance, tensile resistance and torsion resistance, and the plate structure of the main body greatly increases the contact area when the landing gear lands on the ground, so that impact load caused by the self weight of the airplane at the landing moment is dispersed, the capability of resisting the impact load is increased, and the damage to the airplane when the landing gear lands on the ground is reduced to the minimum.
Description
Technical Field
The invention relates to the field of structural design of an undercarriage of an unmanned aerial vehicle, in particular to an undercarriage device for an ultra-light small-sized unmanned aerial vehicle.
Background
The landing gear is an accessory device which is positioned at the lower part of the airplane and is used for supporting the airplane during takeoff and landing or ground taxiing and is used for ground movement, and the landing gear is the only part for supporting the whole airplane. In the design process of the structure of the landing gear of the unmanned aerial vehicle, on one hand, the functional integrity of the landing gear and the harsh weight requirement of the landing gear are considered, the structure of the landing gear needs to be designed skillfully and reasonably, and the material selection is proper, so that the weight of the structure is the lightest; on the other hand, the rigidity and the strength of the landing gear can bear the huge impact caused by the landing of the aircraft, and the integral structure can bear the impact load between the aircraft and the ground when landing.
The design requirements of the take-off and landing modes of a certain ultra-light small unmanned aerial vehicle on multiple working conditions are met, the take-off and landing modes on multiple working conditions such as running, vehicle-mounted, parachuting and ground movement can be met, the structure is simple, the processing is low in price, the weight is further reduced, the maintenance requirement is low, and the take-off and landing mode is changed rapidly. At present, no related design can simultaneously meet the requirements
Disclosure of Invention
In order to adapt to the takeoff and landing modes of multiple working conditions of a novel unmanned aerial vehicle and design indexes of weight reduction, the invention provides a landing gear mechanism suitable for an ultra-light small-sized unmanned aerial vehicle, and the landing gear mechanism can meet the requirements of multiple working conditions of running, vehicle-mounted landing, parachuting, ground movement and the like.
The technical scheme of the invention is as follows:
the take-off and landing device for the ultralight small-sized unmanned aerial vehicle is characterized in that: consists of a skid plate, a vertical tail fixing piece and a pulley mechanism;
according to the size and position of the aircraft vertical tail, two pairs of vertical tail fixing piece clamping grooves with 4 positions are formed in the skid plate, and a fixing piece screw positioning hole is formed between each pair of vertical tail fixing piece clamping grooves;
the vertical tail fixing piece is of a three-surface structure, the bottom surface of the vertical tail fixing piece is provided with a screw hole corresponding to the fixing piece screw positioning hole, and two side surfaces of the vertical tail fixing piece are provided with connecting holes fixedly connected with the vertical tail; the vertical tail fixing piece penetrates through a pair of vertical tail fixing piece clamping grooves from bottom to top, a screw hole in the bottom surface is correspondingly matched with a fixing piece screw positioning hole between the vertical tail fixing piece clamping grooves, and fixing is achieved through a screw;
the skid plate is also provided with 2 square tire limiting holes, and pulley mechanism mounting holes are respectively arranged in front of and behind the square tire limiting holes; the square tire limiting hole close to the rear end of the skid plate is positioned between the two pairs of vertical tail fixing piece clamping grooves;
the pulley mechanism consists of a wheel fork, a wheel shaft and a tire; the top surface of the wheel fork is provided with a square opening with the same size as the square tire limiting hole, and the front and the back of the square opening are respectively provided with a mounting hole corresponding to the positions of the pulley mechanism mounting holes arranged in the front and the back of the square tire limiting hole; the two side surfaces of the wheel fork are provided with corresponding wheel axle holes, the wheel axle is fixedly arranged in the pair of wheel axle holes, and the axis of the wheel axle is positioned in the middle of the square hole; the tire is mounted on the wheel axle;
the pulley mechanism is arranged at the position of the square tire limiting hole of the skid plate in a detachable connection mode.
Furthermore, the number of the fixing piece screw positioning holes between the first vertical tail fixing piece clamping grooves close to the rear end of the skid plate is 2; the number of the fixing piece screw positioning holes between the other pair of opposite tail fixing piece clamping grooves is 3, and the 3 fixing piece screw positioning holes are in a triangular layout.
Furthermore, the front end of the skid plate is provided with an upwarping arc transition section, and the upwarping arc transition section is provided with a square opening.
Furthermore, the skid plate is integrally made of carbon fiber resin matrix composite materials.
Furthermore, when the aircraft adopts the parachute landing mode, the pulley mechanism is dismantled, and the skid plate is in contact with the landing surface, so that the loading area and the bearing capacity are improved.
Advantageous effects
The landing gear main body is a skid plate structure integrally made of carbon fiber resin matrix composite materials, and has good compression resistance, tensile resistance and torsion resistance, and the plate structure of the main body greatly increases the contact area of the landing gear when the landing gear lands on the ground, so that the impact load caused by the self weight of the airplane at the landing moment is dispersed, the impact load resistance of the landing gear main body is increased, and the damage to the landing gear main body is reduced to the minimum. Meanwhile, the undercarriage is provided with the pulley mechanism mounting position, so that the undercarriage has the functions of ground running and landing, vehicle-mounted take-off and parachute landing, and after the pulley mechanism is mounted, the problem that the skid structure cannot freely move on the ground is solved, and the adaptability of the undercarriage to the working condition is improved.
The landing gear main body adopts an integrated forming technology during manufacturing, and has the advantages of simple structure, convenient processing, convenient assembly and easy maintenance and part replacement. In the aspect of weight reduction, the undercarriage is simplified according to a landing mode and a loaded condition, the use of connecting pieces and connecting screws is reduced, the whole undercarriage main body is mainly made of carbon fiber resin matrix composite materials, the weight is obviously reduced on the basis of meeting the design requirements of the undercarriage, and the landing gear has great significance for an aircraft.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1: general structure diagram of landing gear
Wherein, the wheel comprises 1-a skid plate, 2-a vertical tail fixing piece, 3-a tire, 4-a wheel fork and 5-a wheel shaft;
FIG. 2: structure of parachute landing gear
Wherein, 1-the skid board and 2-the vertical tail fixing piece are arranged;
FIG. 3: a vertical tail fixing piece;
figure 4 pulley mechanism
Wherein 3-tyre, 4-wheel fork and 5-wheel shaft.
Detailed Description
In order to enable the aircraft to bear larger impact load and reduce the damage to the aircraft landing gear and the aircraft body, the invention changes the common wheel type landing gear into the skid landing gear, the skid structure landing gear plays a buffer role when the aircraft lands, absorbs the energy caused by the vertical speed when the aircraft lands, bears the impact load when the aircraft lands, and reduces the overload caused by landing impact, and the main structure is shown in figure 1. According to the size and position of the vertical tail of the airplane, two pairs of vertical tail fixing piece clamping grooves with 4 positions and 2 prescription-shaped tire limiting holes are respectively formed in the skid plate. Two vertical tail fixing frames penetrate through the clamping grooves to be fixedly connected with the airplane vertical tail; 2 the prescription tire limit hole is the limit mounting hole corresponding to the corresponding vehicle-mounted fixing device position, so that the undercarriage can not only automatically slide off and land, but also adopt vehicle-mounted take-off and slide off and land when the runway environment is poor.
Meanwhile, if the aircraft lands in an umbrella landing mode, the sliding wheels of the landing gear can be detached, and the landing gear main body is only a sliding skid plate, so that the aircraft has a larger contact area during landing, and the loading capacity of the landing gear is greatly increased. The front section of the skid plate is in upwarping arc transition, so that the forward turning of the aircraft caused by ground obstacles during inertial sliding is effectively avoided, and the aircraft can be protected.
The undercarriage main part mainly adopts carbon fiber composite material, and the mounting adopts duralumin material, and the shaft has adopted the suitable 45 # steel of rigidity and intensity, through the trial and error, this undercarriage simple structure, processing low price, weight further reduce, the maintenance requirement is low when satisfying performance and functional requirement.
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
The landing gear main part of the example design shown in fig. 1 uses skid plate 1 as a main structure, and is provided with two pairs of four vertical tail fixing frame mounting clamping grooves which are symmetrical pairwise and 5 fixing piece screw positioning holes, wherein the number of the fixing piece screw positioning holes between the first vertical tail fixing frame clamping grooves close to the rear end of the skid plate is 2, the number of the fixing piece screw positioning holes between the other vertical tail fixing frame clamping grooves is 3, and the 3 fixing piece screw positioning holes are in a triangular layout, so that on the basis of meeting the strength requirement, the number of the fixed connection structures is reduced as much as possible, and the overall quality of the aircraft is reduced. The two vertical tail fixing pieces 2 can pass through the clamping grooves and are fixed on the skid plate by using screws, and holes are respectively formed in the two side surfaces of each vertical tail fixing piece 2 and are used for fixing the vertical tail; the skid plate is provided with 2 square tire limiting holes which are installation spaces of the pulley mechanism and correspond to the limiting areas of the landing gear on the vehicle-mounted fixing device. The tire limiting holes are formed in the skid plate, so that the height of the side face of the wheel fork can be effectively reduced, and the quality of the wheel fork is reduced.
The whole undercarriage can be used for running takeoff, vehicle takeoff or ground movement.
Fig. 2 is a view showing that the pulley mechanism is removed on the basis of fig. 1, the whole body is composed of a skid plate 1 and 2 vertical tail fixing pieces 2, the pulley mechanism is mainly used for an aircraft landing mode of parachuting, the loaded area and the bearing capacity can be increased, the front section of the skid plate is in upwarping arc transition, and the pulley mechanism can play a role in protecting the aircraft during inertial running.
Functionally, the landing gear main part is the skid plate structure of being made by carbon fiber resin matrix combined material integration, and it has good resistance to compression, tensile, torsion resistance, and the plate structure greatly increased the area of contact when landing gear of main part falls to the ground for the landing receives the impact load that the aircraft dead weight brought in the twinkling of an eye and is dispersed, has increased its ability of resisting impact load, and the damage that receives when falling to the ground reduces minimum. Meanwhile, the undercarriage is provided with the pulley mechanism mounting position, so that the undercarriage has the functions of ground running and landing, vehicle-mounted take-off and parachuting, and after the tire structure is mounted, the problem that the skid structure cannot freely move on the ground is solved, and the adaptability of the undercarriage to the working condition is improved.
The landing gear main body adopts an integrated forming technology during manufacturing, and has the advantages of simple structure, convenient processing, convenient assembly and easy maintenance and part replacement. In the aspect of weight reduction, the undercarriage is simplified according to a landing mode and a loaded condition, the use of connecting pieces and connecting screws is reduced, the whole undercarriage main body is mainly made of carbon fiber resin matrix composite materials, the weight is obviously reduced on the basis of meeting the design requirements of the undercarriage, and the landing gear has great significance for an aircraft.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (5)
1. A take-off and landing device for an ultra-light small-sized unmanned aerial vehicle is characterized in that: consists of a skid plate, a vertical tail fixing piece and a pulley mechanism;
according to the size and position of the aircraft vertical tail, two pairs of vertical tail fixing piece clamping grooves with 4 positions are formed in the skid plate, and a fixing piece screw positioning hole is formed between each pair of vertical tail fixing piece clamping grooves;
the vertical tail fixing piece is of a three-surface structure, the bottom surface of the vertical tail fixing piece is provided with a screw hole corresponding to the fixing piece screw positioning hole, and two side surfaces of the vertical tail fixing piece are provided with connecting holes fixedly connected with the vertical tail; the vertical tail fixing piece penetrates through a pair of vertical tail fixing piece clamping grooves from bottom to top, a screw hole in the bottom surface is correspondingly matched with a fixing piece screw positioning hole between the vertical tail fixing piece clamping grooves, and fixing is achieved through a screw;
the skid plate is also provided with 2 square tire limiting holes, and pulley mechanism mounting holes are respectively arranged in front of and behind the square tire limiting holes; the square tire limiting hole close to the rear end of the skid plate is positioned between the two pairs of vertical tail fixing piece clamping grooves;
the pulley mechanism consists of a wheel fork, a wheel shaft and a tire; the top surface of the wheel fork is provided with a square opening with the same size as the square tire limiting hole, and the front and the back of the square opening are respectively provided with a mounting hole corresponding to the positions of the pulley mechanism mounting holes arranged in the front and the back of the square tire limiting hole; the two side surfaces of the wheel fork are provided with corresponding wheel axle holes, the wheel axle is fixedly arranged in the pair of wheel axle holes, and the axis of the wheel axle is positioned in the middle of the square hole; the tire is mounted on the wheel axle;
the pulley mechanism is arranged at the position of the square tire limiting hole of the skid plate in a detachable connection mode.
2. The take-off and landing device for the ultra-light small-sized unmanned aerial vehicle as claimed in claim 1, wherein: the number of the fixing piece screw positioning holes between the first vertical tail fixing piece clamping grooves close to the rear end of the skid plate is 2; the number of the fixing piece screw positioning holes between the other pair of opposite tail fixing piece clamping grooves is 3, and the 3 fixing piece screw positioning holes are in a triangular layout.
3. The take-off and landing device for the ultra-light small-sized unmanned aerial vehicle as claimed in claim 1, wherein: the front end of the skid plate is provided with an upwarping arc transition section, and the upwarping arc transition section is provided with a square opening.
4. The take-off and landing device for the ultra-light small-sized unmanned aerial vehicle as claimed in claim 1, wherein: the skid plate is integrally made of carbon fiber resin matrix composite materials, the vertical tail fixing piece is made of hard aluminum materials, and the wheel shaft is made of No. 45 steel.
5. The take-off and landing device for the ultra-light small-sized unmanned aerial vehicle as claimed in claim 1, wherein: when the aircraft adopts the parachute landing mode, the pulley mechanism is dismantled, and the skid plate is in contact with the landing surface, so that the loading area and the bearing capacity are improved.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010491570.0A CN111532421A (en) | 2020-06-02 | 2020-06-02 | A take-off and landing device for ultralight small-size unmanned vehicles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010491570.0A CN111532421A (en) | 2020-06-02 | 2020-06-02 | A take-off and landing device for ultralight small-size unmanned vehicles |
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| Publication Number | Publication Date |
|---|---|
| CN111532421A true CN111532421A (en) | 2020-08-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010491570.0A Pending CN111532421A (en) | 2020-06-02 | 2020-06-02 | A take-off and landing device for ultralight small-size unmanned vehicles |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113212743A (en) * | 2021-06-25 | 2021-08-06 | 深圳市大京科技有限公司 | Unmanned aerial vehicle convenient to multi-angle is shot and is had shock attenuation descending function |
| CN114016613A (en) * | 2021-11-16 | 2022-02-08 | 西安长峰机电研究所 | High-bearing composite structure light skid |
-
2020
- 2020-06-02 CN CN202010491570.0A patent/CN111532421A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113212743A (en) * | 2021-06-25 | 2021-08-06 | 深圳市大京科技有限公司 | Unmanned aerial vehicle convenient to multi-angle is shot and is had shock attenuation descending function |
| CN114016613A (en) * | 2021-11-16 | 2022-02-08 | 西安长峰机电研究所 | High-bearing composite structure light skid |
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