CN207565839U - A kind of novel fixed-wing unmanned plane using solar recharging - Google Patents

Abstract

A new type of fixed-wing unmanned aerial vehicle that uses solar energy to charge, including a fuselage, wings, tail, take-off and landing pulleys, and solar panels. The front end of the fuselage is fixed with a drive motor. A signal receiver is provided on the top of the wing, and two-stage flaps are provided on the trailing edge of the wing. The two-stage flaps include a first flap and a second flap, and the first flap and the second flap pass through the retractable system. Connected with the wing, the solar panels are respectively fixed on the top of the wing, the first flap and the second flap, an autopilot and a battery are fixed inside the fuselage, the solar panel is connected to the battery, and the battery is connected to the automatic The pilot is connected, and the autopilot is respectively connected with the GPS locator, FPV camera, signal receiver, steering gear, electronic governor and retractable system, and the electronic governor is connected with the driving motor. The fixed-wing unmanned aerial vehicle not only improves endurance, but also improves the safety performance of its landing.

Description

A new fixed-wing drone powered by solar energy

technical field

The utility model relates to the field of unmanned aerial vehicles, in particular to a novel fixed-wing unmanned aerial vehicle charged by solar energy.

Background technique

UAV is an unmanned aircraft operated by radio remote control equipment and self-contained program control device. Compared with traditional manned aircraft, UAV is suitable for tasks under various environmental conditions, especially tasks under harsh conditions . With the deepening of drone research, the cost of drones is lower, which directly provides strong conditions for the large-scale promotion of drones. At present, drones are used in aerial photography, agriculture, plant protection, micro-express delivery, and disaster relief. , surveying and mapping, power inspection and other fields have been widely used.

The commonly used UAVs are divided into multi-rotor UAVs and fixed-wing UAVs. Due to their smaller size, multi-rotor UAVs are more suitable for detection, aerial photography and other fields, but they are small in size, poor in load capacity and The endurance is poor, and at the same time, the stability is not as good as that of fixed-wing UAVs in harsh environments, while the carrying capacity of fixed-wing UAVs is higher than that of rotor UAVs. More equipment to perform a wider range of tasks.

However, because fixed-wing UAVs mostly use electric energy as the only source of power, the endurance limits the development of fixed-wing UAVs. The existing technology mostly uses solar energy to charge its batteries to improve endurance, but it is not suitable for fixed-wing UAVs. Man-machine structural changes, only relying on solar energy to provide electric power to extend the performance is very limited. At the same time, due to the lack of more efficient shock absorption measures, the existing fixed-wing UAVs are easy to damage or cause other damage during the landing process. Damage to precision instruments carried.

Utility model content

In order to solve the above problems, the utility model designs a new type of fixed-wing unmanned aerial vehicle that uses solar energy to charge the battery. The performance is better, the energy consumption is reduced, and the electric energy converted from solar energy and the electric energy of the battery are used more efficiently, thereby greatly improving the endurance of the fixed-wing UAV.

In order to achieve the above-mentioned technical purpose and achieve the above-mentioned technical effect, the utility model is achieved through the following technical solutions:

A new type of fixed-wing unmanned aerial vehicle that uses solar energy to charge, including a fuselage, wings, tail, take-off and landing pulleys, and solar panels. The top of the top is provided with a signal receiver, and it is characterized in that: the trailing edge of the wing is provided with two-stage flaps, and the two-stage flaps include a first flap and a second flap, and the first flap and the second flap The retractable system is connected to the wing, the solar panels are respectively fixed on the top of the wing, the first flap and the second flap, the autopilot and the battery are fixed inside the fuselage, and the solar panel is connected to the battery , the solar panel is connected to the battery with an inverter, the battery is connected to the autopilot, and the autopilot is connected to the GPS locator, FPV camera, signal receiver, steering gear, electronic governor and The retractable system is connected, and the electronic governor is connected with the driving motor.

Further, the front end of the fuselage is provided with anti-collision seesaws, the anti-collision seesaws are respectively fixed on the take-off and landing pulleys on both sides, the anti-collision seesaws are fixed with shock-absorbing supports, and the upper ends of the shock-absorbing supports are fixed on the machine the bottom of the body.

Further, the retractable system is composed of a retractable motor, a folding storage mechanism, a bracket, a first connecting rod, a second connecting rod, a third connecting rod, a connecting plate, a fourth connecting rod, a fifth connecting rod, a A multi-link system composed of six links and the seventh link, the first link is fixed on the rotating shaft of the retractable motor, the first link is hinged to the second link, one end of the second link is fixed on the bracket and the other One end is hinged to the connecting plate, the third connecting rod is hinged to the second connecting rod, the fourth connecting rod is hinged to the third connecting rod, the fifth connecting rod is hinged to the fourth connecting rod, and one end of the sixth connecting rod is hinged to the fifth connecting rod And the other end is hinged with the seventh connecting rod, the connecting plate is fixed on the right end of the first flap, the fifth connecting rod is fixed on the side of the first flap, and one end of the sixth connecting rod is fixed on the first flap In the middle of the side of the first flap, there is a chute on the left end of the side of the first flap, the seventh connecting rod is fixed on the right end of the second flap, the seventh connecting rod can slide to the left along the chute and pull the second flap. Flaps retract or extend.

Further, the internal assembly of the autopilot has a communication module, and the communication protocol adopted by the communication module is one of 2G/3G/4G/WIFI/BlueTooth/ZigBee.

The beneficial effects of the utility model are: the UAV uses solar energy to charge the storage battery, and at the same time, the wing of the fixed-wing UAV is improved to make its aerodynamic performance better, reduce energy consumption, and make the electric energy converted from solar energy and the storage battery The power usage efficiency of the drone is higher, which greatly improves the endurance of the fixed-wing UAV, and when the UAV lands, it can effectively protect the fuselage and the precision instruments it carries, and the safety is higher.

Description of drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the accompanying drawings required for the description of the embodiments. Obviously, the accompanying drawings in the following description are only some embodiments of the present invention. For those skilled in the art, other drawings can also be obtained based on these drawings without creative effort.

Figure 1 is a schematic diagram of the overall structure of a new type of fixed-wing unmanned aerial vehicle charged by solar energy;

Fig. 2 is a kind of structural schematic diagram of each component of the novel fixed-wing unmanned aerial vehicle that utilizes solar energy to charge;

Fig. 3 is a schematic diagram of the connecting structure of the flap of a novel fixed-wing unmanned aerial vehicle utilizing solar energy charging;

Fig. 4 is a schematic diagram of wing aerodynamic optimization of a novel fixed-wing unmanned aerial vehicle utilizing solar energy charging;

Fig. 5 is a structural block diagram of a new type of fixed-wing unmanned aerial vehicle charged by solar energy.

In the accompanying drawings, the list of parts represented by each label is as follows:

1-Fuselage, 11-Wing, 12-Flap, 13-Drive Motor, 14-Propeller Blade, 15-Shock Absorbing Support, 16-Signal Receiver, 17-Autopilot, 18-Battery, 19-Rudder machine, 2-solar panel, 3-folding storage mechanism, 31-bracket, 32-first connecting rod, 33-second connecting rod, 34-third connecting rod, 35-connecting plate, 36-fourth connecting rod , 37-fifth connecting rod, 38-sixth connecting rod, 39-seventh connecting rod, 111-retractable motor, 121-first flap, 122-second flap, 123-chute, 151-up Lower pulley, 152-shock absorbing support, 153-anti-collision rocker, 171-GPS locator, 172-FPV camera, 173-electronic governor, 174-retractable system, 175-communication module, 181-inverter .

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. example. Based on the embodiments of the present utility model, all other embodiments obtained by persons of ordinary skill in the art without creative efforts belong to the scope of protection of the present utility model.

Referring to shown in Fig. 1-5, a kind of novel fixed-wing unmanned aerial vehicle utilizing solar energy charging, comprises fuselage (1), wing (11), empennage, take-off and landing pulley (151) and solar panel (2), The front end of fuselage (1) is fixed with driving motor (13), fixed propeller blade (14) on the rotating shaft of driving motor (13), and the top of fuselage (1) is provided with signal receiver (16), and wing (11 ) trailing edge is provided with two-stage flap (12), and two-stage flap comprises first flap (121) and second flap (122), and first flap (121) and second flap (122) pass Retractable system (174) is connected with wing (11), and solar panel (2) is respectively fixed on the top of wing (11), the first flap (121) and the second flap (122), fuselage ( 1) An autopilot (17) and a storage battery (18) are fixed inside, the solar panel (2) is connected to the storage battery (18), and an inverter is provided on the line connecting the solar panel (2) to the storage battery (18) (181), storage battery (18) is connected with autopilot (17), and autopilot (17) is respectively connected with GPS locator (171), FPV camera (172), signal receiver (16), steering gear (19) , the electronic governor (173) is connected with the retractable system (174), and the electronic governor (173) is connected with the drive motor (13).

Wherein, the front end of the fuselage (1) is provided with an anti-collision seesaw (153), and the anti-collision seesaw (153) is respectively fixed on the take-off and landing pulleys (151) on both sides, and the anti-collision seesaw (153) A shock-absorbing support (152) is fixed on the top, and the upper end of the shock-absorbing support (152) is fixed on the bottom of the fuselage. The shock-absorbing support (152) in this embodiment is made of an elastic rod material. When landing, the shock-absorbing support (152) can absorb the impact energy, and the anti-collision seesaw (153) can prevent the head of the fuselage (1) from hitting the ground simultaneously, so as to improve the safety performance of its landing.

Wherein, the retractable system (174) is composed of a retractable motor (111), a folding storage mechanism (3), a bracket (31), a first connecting rod (32), a second connecting rod (33), a A multi-link system consisting of three links (34), connecting plates (35), fourth links (36), fifth links (37), sixth links (38) and seventh links (39) , the first connecting rod (32) is fixed on the rotating shaft of the retractable motor (111), the first connecting rod (32) is hinged with the second connecting rod (33), and one end of the second connecting rod (33) is fixed on the bracket (31 ) and the other end is hinged with the connecting plate (35), the third connecting rod (34) is hinged with the second connecting rod (32), the fourth connecting rod (36) is hinged with the third connecting rod (34), and the fifth connecting rod Rod (37) is hinged with the fourth connecting rod (36), one end of the sixth connecting rod (38) is hinged with the fifth connecting rod (37) and the other end is hinged with the seventh connecting rod (39), and the connecting plate ( 35) is fixed on the right end of the first flap (121), the fifth connecting rod (37) is fixed on the side of the first flap (121), and one end of the sixth connecting rod (38) is fixed on the first flap ( In the middle of the side of 121), there is a chute (123) on the left end of the side of the first flap (121), and the seventh connecting rod (39) is fixed on the right end of the second flap (122). The seven connecting rods (39) can slide to the left along the chute (123) and pull the second flap (122) to contract or expand.

The airflow optimization principle of the flap in the present embodiment is: when the flap (2) on the unfolded wing that the autopilot (17) receives the ground station to send, the autopilot (17) will retract the electric motor (111) Output high level, the retractable motor (111) drives the retractable system that is the multi-link system in the present embodiment to extend outwards, and now the first flap (121) and the second flap (122) are facing the wing ( 11) The rear is deployed, and the airflow above the wing (11) has a longer journey, while the airflow below the wing (11) flows along the bottom of the wing. When the airflow at the bottom flows to the first flap (121) and the second During two flaps (122), the air-flow forms two branches, and one airflow supports the upper surface flow of the first flap (121), and one flows along the upper surface of the second flap (122), and the wing (11 ) bottom, the bottom of the first flap (121) and the bottom of the second flap (122) have a faster flow rate, forming a Coanda effect, and the lift of the wing (1) is further improved, thereby saving the work consumption of the drive motor (13) of electric energy.

Because the tops of the wing (11), the first flap (121) and the second flap (122) are respectively fixed with solar panels (2), when the sun is abundant, the solar panels (2) convert solar energy into Electric energy, and after being rectified, filtered and inverted by the inverter (181), becomes the electric energy that the storage battery (18) can store, further improving the endurance of the fixed-wing unmanned aerial vehicle.

In the description of this specification, descriptions referring to the terms "one embodiment", "example", "specific example" and the like mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in the description of the present invention. In at least one embodiment or example. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example.

The preferred embodiments of the present invention disclosed above are only used to help explain the present invention. The preferred embodiments do not exhaust all details, nor do they limit the utility model to the specific implementations described. Obviously, many modifications and variations can be made based on the contents of this specification. This specification selects and specifically describes these embodiments in order to better explain the principle and practical application of the utility model, so that those skilled in the art can well understand and utilize the utility model. The invention is to be limited only by the claims and their full scope and equivalents.

Claims (5)

1. a kind of novel fixed-wing unmanned plane using solar recharging, including fuselage, wing, empennage, landing pulley and the sun Energy solar panel, fuselage are fixedly arranged at the front end with driving motor, screw blade are fixed in the shaft of driving motor, and the top of fuselage is equipped with Signal receiver, it is characterised in that：The trailing edge is equipped with two-stage wing flap, and two-stage wing flap includes the first wing flap and second flap The wing, the first wing flap and the second wing flap are connect by extension and retraction system with wing, the solar panel be individually fixed in wing, The top of first wing flap and the second wing flap, fuselage interior are fixed with automatic pilot and accumulator, solar panel and electric power storage Pond connects, and accumulator connect with automatic pilot, automatic pilot respectively with GPS positioning instrument, FPV cameras, signal receiver, Steering engine, electron speed regulator are connected with extension and retraction system, and electron speed regulator is connect with driving motor.

2. a kind of novel fixed-wing unmanned plane using solar recharging according to claim 1, it is characterised in that：It is described Front fuselage be equipped with anticollision wraping plate, anticollision wraping plate is individually fixed on the landing pulley of both sides, is fixed with and subtracts on anticollision wraping plate Shake support, the bottom of fuselage is fixed in the upper end of shock-absorbing support.

3. a kind of novel fixed-wing unmanned plane using solar recharging according to claim 1, it is characterised in that：It is described Extension and retraction system be by folding and unfolding motor, folding storage mechanism, stent, first connecting rod, second connecting rod, third connecting rod, connecting plate, The multi link system that fourth link, the 5th connecting rod, six-bar linkage and seven-link assembly form, first connecting rod are fixed on folding and unfolding motor Shaft on, head rod is hinged with the second connecting rod, and second connecting rod one end is fixed on stent and the other end and connection Plate is hinged, and third connecting rod is hinged with the second connecting rod, and the 4th connecting rod is hinged with third connecting rod, the 5th connecting rod and the 4th Connecting rod is hinged, and the 6th connecting rod one end is hinged with the 5th connecting rod and the other end is hinged with the 7th connecting rod, the connection Plate is fixed on the right end of the first wing flap, and the 5th connecting rod is fixed on the side of the first wing flap, and one end of six-bar linkage is fixed on The side middle of first wing flap is provided with sliding slot on the side left end of the first wing flap, and seven-link assembly is fixed on the right side of the second wing flap On the head of side, seven-link assembly can to the left slide along sliding slot and the second wing flap is pulled to shrink or be unfolded.

4. a kind of novel fixed-wing unmanned plane using solar recharging according to claim 1, it is characterised in that：It is described The circuit that is connect with accumulator of solar panel be equipped with inverter.

5. a kind of novel fixed-wing unmanned plane using solar recharging according to claim 1, it is characterised in that：It is described Automatic pilot inner set communication module, the communications protocol that communication module uses is 2G/3G/4G/WIFI/BlueTooth/ One kind in ZigBee.