Gliding type solar unmanned aerial vehicle device replacing satellite communication

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a gliding type solar unmanned aerial vehicle device replacing satellite communication, which comprises an unmanned aerial vehicle body, a storage cavity is formed in the rear end of the unmanned aerial vehicle body, and a parachute bag is placed in the storage cavity. A pop-up cover is installed on the top of the unmanned aerial vehicle body and located on the outer side of the storage cavity, a connecting block is fixedly connected to the front end of the pop-up cover, clamping blocks are fixedly connected to the top of the unmanned aerial vehicle body and located at the left end and the right end of the connecting block, and a locking block is fixedly connected to the rear end of the pop-up cover; compared with an existing gliding type solar unmanned aerial vehicle device replacing satellite communication, the gliding type solar unmanned aerial vehicle device can guarantee safe landing when a flight fault occurs due to a power fault or weather influence through the design, and the gliding type solar unmanned aerial vehicle device is convenient to use. And damage caused by falling impact force is avoided.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a gliding solar-powered UAV device that can replace satellite communication. Background Technology

[0002] Solar-powered drones utilize solar cells to provide electricity to drive motors that power propellers. They feature ultra-long endurance, potentially lasting from months to years, and can fly at altitudes exceeding 20,000 meters. They can operate over wide areas, possessing "quasi-satellite" characteristics, and offer advantages such as flexible deployment and cost-effectiveness. They can be widely applied in the field of military-civilian integration, including public welfare sectors such as early warning of major natural disasters, routine maritime surveillance, emergency rescue and disaster relief, and counter-terrorism and stability maintenance, as well as commercial and industrial sectors such as internet wireless access, mobile communications, and digital television signal broadcasting in remote areas.

[0003] According to the search, CN111776229A discloses a gliding solar-powered drone device as an alternative to satellite communication, which includes a drone body and a solar cell module device installed on the outer surface of the drone body. The drone body is equipped with a deployable flexible solar cell module device, and the drone body is equipped with a deployable wind power generation device inside the drone body.

[0004] The aforementioned patent enables drones to effectively utilize high-altitude wind power for wind power generation, thereby greatly increasing the drone's continuous flight time. However, due to the high operating altitude, when a power failure occurs or a flight failure is caused by weather conditions, the drone body is not equipped with a protective and shock-absorbing structure. During landing, the upper part of the drone body cannot be protected and buffered, and the drone may be damaged due to excessive impact force.

[0005] Therefore, it is of great importance to design a gliding solar-powered drone device to replace satellite communication and solve the above-mentioned shortcomings. Utility Model Content

[0006] To address the shortcomings of existing technologies, this utility model designs a gliding solar-powered drone device to replace satellite communication. This device aims to solve the technical problem that existing gliding solar-powered drone devices that replace satellite communication do not have protective and shock-absorbing structures on their bodies, and therefore cannot protect and cushion the drone body during landing, which may cause damage to the drone due to excessive impact force.

[0007] To achieve the above objectives, this utility model provides the following technical solution:

[0008] A gliding solar-powered unmanned aerial vehicle (UAV) device as an alternative to satellite communication includes a UAV body. A storage cavity is located inside the rear end of the UAV body, and a parachute pack is placed inside the storage cavity. A pop-out cover is installed on the top of the UAV body outside the storage cavity. A connecting block is fixedly connected to the front end of the pop-out cover. Locking blocks are fixedly connected to the left and right ends of the connecting block on the top of the UAV body. A locking block is fixedly connected to the rear end of the pop-out cover. An unlocking mechanism is installed on the top of the UAV body at a position corresponding to the locking block. Sub-frames are fixedly installed on the left and right ends of the bottom of the UAV body. Buffer mechanisms are installed at the front and rear ends of the bottom of both sets of sub-frames.

[0009] As a preferred embodiment of this utility model, wings are fixedly installed at both ends of the UAV body, and a first flexible solar panel is installed on the surface of both sets of wings. A tail fin is fixedly installed between the two sets of sub-frames, and a second flexible solar panel is installed on the surface of both ends of the tail fin.

[0010] As a preferred embodiment of this utility model, the rear end of the UAV body is equipped with a power fan blade, and both ends of the two sets of sub-frames are equipped with climbing fan blades.

[0011] As a preferred embodiment of this utility model, a closing groove is provided at the top of the storage cavity corresponding to the position of the pop-up cover, and two sets of springs are fixedly connected to the rear end inside the closing groove.

[0012] As a preferred embodiment of this utility model, the left and right ends of the connecting block are fixedly connected with rotating shafts, and the inner sides of the two sets of card blocks are provided with card slots, and the rotating shafts extend into the inner side of the card slots.

[0013] As a preferred embodiment of this utility model, the unlocking mechanism includes a fixed box fixedly connected to the top of the drone body and located inside the locking block. Locking pins are slidably connected to both the left and right ends of the fixed box, and both sets of locking pins are inserted into the left and right ends of the locking block. A moving block is fixedly connected to the opposite end of each set of locking pins. A bidirectional threaded rod is rotatably connected to the top of the fixed box. A micro motor is fixedly installed at the right end of the top of the fixed box, and the drive end of the micro motor is fixedly connected to the right end of the bidirectional threaded rod. Connecting sleeves are threaded to both ends of the bidirectional threaded rod, and the connecting sleeves are rotatably connected to the top of the moving block.

[0014] As a preferred embodiment of this utility model, a protective cover is fixedly installed on the top of the fixed box, and the movable block is slidably connected to the inside of the fixed box through a movable groove.

[0015] As a preferred embodiment of this utility model, the buffer mechanism includes diagonal bracing arms fixedly installed at the front and rear ends of the bottom of the sub-frame. The bottom end of the diagonal bracing arm is rotatably connected to a support foot. A shock absorber is installed between the support foot and the diagonal bracing arm. The two ends of the shock absorber are rotatably connected to the diagonal bracing arm and the support foot, respectively.

[0016] As a preferred embodiment of this utility model, both the front and rear ends of the bottom of the support foot are rotatably connected to a locking plate, and wear plates are locked onto the outer side of each locking plate. Rubber buffer pads are fixedly connected to the bottom of each set of wear plates.

[0017] Compared with the prior art, the beneficial effects of this utility model are:

[0018] 1. In this utility model, through the coordinated design of the drone body, storage cavity, parachute pack, ejection cover, connecting block, locking block, locking block and unlocking mechanism, when a power failure or flight failure caused by weather occurs, the unlocking mechanism releases the locking block. At this time, under the action of the spring, the rear end of the ejection cover is ejected from the inside of the closing groove, thereby quickly opening the ejection cover. Subsequently, the parachute pack inside the drone body's landing storage cavity deploys to assist in landing, thereby protecting the drone body and ensuring its safe landing.

[0019] 2. In this utility model, through the design of the buffer mechanism, when the drone body lands, the support feet are subjected to force after contact with the ground, and the shock absorber buffers the impact, thereby ensuring the stability of the drone body during landing and avoiding damage to the drone body caused by the landing impact. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0021] Figure 2 for Figure 1 Enlarged view of point A in the middle;

[0022] Figure 3 This is a schematic diagram of the deployment structure of the parachute pack of this utility model;

[0023] Figure 4 for Figure 3 Enlarged view at point B in the middle;

[0024] Figure 5 This is a schematic diagram of the top structure of the fixing box of this utility model;

[0025] Figure 6 This is a schematic diagram of the internal structure of the fixing box of this utility model;

[0026] Figure 7 This is a schematic diagram of the buffer mechanism structure of this utility model;

[0027] Figure 8 for Figure 7 Enlarged view of point C in the middle.

[0028] In the diagram: 1. UAV body; 101. Wing; 102. First flexible solar panel; 103. Tail fin; 104. Second flexible solar panel; 105. Power fan blade; 106. Climbing fan blade; 2. Storage cavity; 3. Parachute pack; 4. Ejection cover; 401. Closing slot; 402. Spring; 5. Connecting block; 501. Shaft; 502. Slot; 6. Locking block; 7. Locking block; 8. Unlocking mechanism; 801. Fixing box; 802. Locking pin; 803. Moving block; 804. Bidirectional threaded rod; 805. Micro motor; 806. Connecting sleeve; 807. Protective cover; 808. Moving slot; 9. Sub-frame; 10. Buffer mechanism; 1001. Diagonal brace arm; 1002. Support foot; 1003. Shock absorber; 1004. Locking plate; 1005. Wear plate; 1006. Rubber buffer pad. Detailed Implementation

[0029] The technical solutions of the present utility model will be clearly and completely described below with reference to the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the protection scope of the present utility model.

[0030] Example: Please refer to Figures 1-8 This utility model provides a technical solution:

[0031] A gliding solar-powered unmanned aerial vehicle (UAV) device that can replace satellite communication includes a UAV body 1. A storage cavity 2 is opened inside the rear end of the UAV body 1, and a parachute pack 3 is placed inside the storage cavity 2. An ejection cover 4 is installed on the top of the UAV body 1 and outside the storage cavity 2. A connecting block 5 is fixedly connected to the front end of the ejection cover 4. Locking blocks 6 are fixedly connected to the top of the UAV body 1 and at both ends of the connecting block 5. A locking block 7 is fixedly connected to the rear end of the ejection cover 4. An unlocking mechanism 8 is installed on the top of the UAV body 1 at a position corresponding to the locking block 7. Sub-frames 9 are fixedly installed on both the left and right ends of the bottom of the UAV body 1. Buffer mechanisms 10 are installed at the front and rear ends of the bottom of the two sets of sub-frames 9.

[0032] First, wings 101 are fixedly installed on both the left and right ends of the drone body 1. First flexible solar panels 102 are installed on the surface of both wings 101. Tail 103 is fixedly installed between the two sets of sub-frames 9. Second flexible solar panels 104 are installed on the surface of both the left and right ends of the tail 103. The drone body 1 is powered by the first flexible solar panels 102 on the wings 101 and the second flexible solar panels 104 on the tail 103, which greatly improves the endurance of the drone body 1.

[0033] Furthermore, a powered fan blade 105 is installed at the rear end of the drone body 1, and climbing fan blades 106 are installed at both the front and rear ends of the two sets of sub-frames 9. When the drone body 1 is in use, it is propelled by the powered fan blade 105, while the climbing fan blades 106 on the sub-frames 9 enable the drone body 1 to climb to the working height on its own. This eliminates the need for additional vehicles to transport it to the corresponding height for deployment, which not only improves the ease of use of the drone body 1, but also allows the multiple climbing fan blades 106 to adjust the working height according to work requirements and adjust the balance of the drone body 1, thereby improving the working stability of the drone body 1.

[0034] Then, a closing groove 401 is provided at the top of the storage cavity 2 corresponding to the position of the pop-out cover 4. Two sets of springs 402 are fixedly connected to the rear end inside the closing groove 401. When the pop-out cover 4 is closed, it is located inside the closing groove 401. When a power failure or flight failure is caused by weather, the locking block 7 is unlocked by the unlocking mechanism 8. At this time, under the action of the spring 402, the rear end of the pop-out cover 4 is popped out from the inside of the closing groove 401, thereby quickly popping out and opening the pop-out cover 4. Subsequently, the parachute pack 3 inside the landing storage cavity 2 of the UAV body 1 deploys to assist in landing, thereby protecting the UAV body 1 and ensuring its safe landing.

[0035] Furthermore, the left and right ends of the connecting block 5 are fixedly connected with a rotating shaft 501, and the inner sides of the two sets of locking blocks 6 are provided with locking slots 502, and the rotating shaft 501 extends to the inner side of the locking slot 502. When the rear end of the pop-out cover 4 pops out, the rotating shaft 501 rotates inside the locking slot 502 and then comes out from the notch on the outside of the locking slot 502, so that the pop-out cover 4 can be removed from the drone body 1 to avoid affecting the parachute pack 3.

[0036] The unlocking mechanism 8 includes a fixed box 801 fixedly connected to the top of the drone body 1 and located inside the locking block 7. Locking pins 802 are slidably connected to both the left and right ends of the fixed box 801, and both sets of locking pins 802 are inserted into the left and right ends of the locking block 7. A moving block 803 is fixedly connected to the opposite end of each set of locking pins 802. A bidirectional threaded rod 804 is rotatably connected to the top of the fixed box 801. A micro motor 805 is fixedly installed on the right end of the top of the fixed box 801, and the drive end of the micro motor 805 is fixedly connected to the right end of the bidirectional threaded rod 804. Both ends of the device are threaded with connecting sleeves 806, and the connecting sleeves 806 are rotatably connected to the top of the moving block 803. When the pop-out cover 4 is closed, the locking pin 802 is inserted into the insertion hole inside the locking block 7, thereby fixing the rear end of the pop-out cover 4. When a power failure occurs or the flight fails due to weather conditions, the micro motor 805 is started to drive the bidirectional threaded rod 804 to rotate. Under the connection of the connecting sleeves 806, the two sets of moving blocks 803 move synchronously. The moving blocks 803 drive the locking pin 802 to retract into the interior of the fixing box 801, thereby releasing the fixation of the pop-out cover 4 and allowing it to pop out.

[0037] Furthermore, a protective cover 807 is fixedly installed on the top of the fixed box 801, and the moving block 803 is slidably connected to the inside of the fixed box 801 through the moving groove 808. The protective cover 807 protects the top structure of the fixed box 801. When the bidirectional threaded rod 804 rotates, the moving block 803 moves stably in the moving groove 808.

[0038] Secondly, the buffer mechanism 10 includes a diagonal support arm 1001 fixedly installed at the front and rear ends of the bottom of the sub-frame 9. The bottom end of the diagonal support arm 1001 is rotatably connected to a support foot 1002. A shock absorber 1003 is installed between the support foot 1002 and the diagonal support arm 1001. The two ends of the shock absorber 1003 are rotatably connected to the diagonal support arm 1001 and the support foot 1002, respectively. When the UAV body 1 lands, the support foot 1002 is subjected to force after contacting the ground and is buffered by the shock absorber 1003, thereby ensuring the stability of the UAV body 1 during landing and avoiding damage to the UAV body 1 caused by the landing impact.

[0039] Finally, the front and rear ends of the bottom of the support foot 1002 are rotatably connected to the clamping plate 1004. The outer side of the clamping plate 1004 is clamped with the wear piece 1005. The bottom of the multiple sets of wear pieces 1005 are fixedly connected with the rubber buffer pad 1006. When the support foot 1002 contacts the ground, the rubber buffer pad 1006 contacts the ground first to buffer. At the same time, after the rubber buffer pad 1006 and the wear piece 1005 are damaged, they can be separated from the clamping plate 1004, which further facilitates the replacement and maintenance of the parts.

[0040] In this embodiment, the specific implementation scenario is as follows: When the pop-out cover 4 is closed, the locking pin 802 is inserted into the insertion hole inside the locking block 7, thereby fixing the rear end of the pop-out cover 4. When a power failure occurs or the flight is affected by weather, the micro motor 805 is started to drive the bidirectional threaded rod 804 to rotate. Under the connection of the connecting sleeve 806, the two sets of moving blocks 803 move synchronously. The moving blocks 803 drive the locking pin 802 to retract into the interior of the fixing box 801, thereby releasing the fixation of the pop-out cover 4. At this time, under the action of the spring 402, the rear end of the pop-out cover 4 is popped out from the inside of the closing groove 401. The rotating shaft 501 rotates inside the slot 502 and then disengages from the notch on the outside of the slot 502, thereby allowing the pop-out cover 4 to be ejected. The cover 4 detaches from the drone body 1 to avoid affecting the parachute pack 3. Subsequently, the parachute pack 3 inside the landing storage cavity 2 of the drone body 1 deploys to assist in landing, thereby protecting the drone body 1 and ensuring its safe landing. When the drone body 1 lands, the support foot 1002 contacts the ground and is cushioned by the shock absorber 1003, thereby ensuring the stability of the drone body 1 during landing and preventing damage to the drone body 1 from the impact of landing. The entire operation process is simple and convenient. Compared with existing gliding solar-powered drone devices that replace satellite communication, this utility model, through its design, can ensure its safe landing and prevent damage caused by landing impact when there is a power failure or flight failure caused by weather.

[0041] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A gliding solar-powered unmanned aerial vehicle (UAV) device as an alternative to satellite communication, comprising the UAV body (1), characterized in that: The drone body (1) has a storage cavity (2) inside its rear end. A parachute pack (3) is placed inside the storage cavity (2). A pop-out cover (4) is installed on the top of the drone body (1) and outside the storage cavity (2). A connecting block (5) is fixedly connected to the front end of the pop-out cover (4). A locking block (6) is fixedly connected to the top of the drone body (1) and at both ends of the connecting block (5). A locking block (7) is fixedly connected to the rear end of the pop-out cover (4). An unlocking mechanism (8) is installed at the position corresponding to the locking block (7) on the top of the drone body (1). Sub-frames (9) are fixedly installed at both ends of the bottom of the drone body (1). Buffer mechanisms (10) are installed at the front and rear ends of the bottom of the two sets of sub-frames (9).

2. The gliding solar-powered unmanned aerial vehicle (UAV) device as an alternative to satellite communication according to claim 1, characterized in that: The UAV body (1) has wings (101) fixedly installed at both ends. The surfaces of the two sets of wings (101) are equipped with first flexible solar panels (102). The two sets of sub-frames (9) are fixedly installed with tail fins (103). The surfaces of the left and right ends of the tail fins (103) are equipped with second flexible solar panels (104).

3. The gliding solar-powered unmanned aerial vehicle (UAV) device as an alternative to satellite communication according to claim 1, characterized in that: The rear end of the UAV body (1) is equipped with a power fan blade (105), and the front and rear ends of the two sets of sub-frames (9) are equipped with climbing fan blades (106).

4. The gliding solar-powered unmanned aerial vehicle (UAV) device as an alternative to satellite communication according to claim 1, characterized in that: A closing groove (401) is provided at the top of the storage cavity (2) at a position corresponding to the pop-up cover (4), and two sets of springs (402) are fixedly connected to the rear end inside the closing groove (401).

5. A gliding solar-powered unmanned aerial vehicle (UAV) device as an alternative to satellite communication according to claim 1, characterized in that: The left and right ends of the connecting block (5) are fixedly connected with rotating shafts (501), and the inner sides of the two sets of card blocks (6) are provided with card slots (502), and the rotating shafts (501) extend to the inner side of the card slots (502).

6. A gliding solar-powered unmanned aerial vehicle (UAV) device as an alternative to satellite communication according to claim 1, characterized in that: The unlocking mechanism (8) includes a fixed box (801) fixedly connected to the top of the UAV body (1) and located inside the locking block (7). The left and right ends of the fixed box (801) are slidably connected with locking pins (802), and both sets of locking pins (802) are inserted into the left and right ends of the locking block (7). The opposite ends of the two sets of locking pins (802) are fixedly connected with moving blocks (803). The top of the fixed box (801) is rotatably connected with a bidirectional threaded rod (804). The right end of the top of the fixed box (801) is fixedly installed with a micro motor (805), and the driving end of the micro motor (805) is fixedly connected to the right end of the bidirectional threaded rod (804). Both ends of the bidirectional threaded rod (804) are threadedly connected with connecting sleeves (806), and the connecting sleeves (806) are rotatably connected to the top of the moving block (803).

7. A gliding solar-powered unmanned aerial vehicle (UAV) device as an alternative to satellite communication according to claim 6, characterized in that: A protective cover (807) is fixedly installed on the top of the fixed box (801), and the movable block (803) is slidably connected to the inside of the fixed box (801) through the movable groove (808).

8. A gliding solar-powered unmanned aerial vehicle (UAV) device as an alternative to satellite communication according to claim 1, characterized in that: The buffer mechanism (10) includes a diagonal brace (1001) fixedly installed at the front and rear ends of the bottom of the subframe (9). The bottom end of the diagonal brace (1001) is rotatably connected to a support foot (1002). A shock absorber (1003) is installed between the support foot (1002) and the diagonal brace (1001). The two ends of the shock absorber (1003) are rotatably connected to the diagonal brace (1001) and the support foot (1002) respectively.

9. A gliding solar-powered unmanned aerial vehicle (UAV) device as an alternative to satellite communication according to claim 8, characterized in that: The front and rear ends of the bottom of the support foot (1002) are rotatably connected with a clamping plate (1004), and wear plates (1005) are clamped on the outer side of the clamping plate (1004). Rubber buffer pads (1006) are fixedly connected to the bottom of the multiple sets of wear plates (1005).

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