Mounting structure for navigation of unmanned aerial vehicle and control surface adjusting mechanism
By combining buffer components and air curtain components, the problem of vibration interference in the UAV navigation module was solved, achieving full-cycle vibration isolation and ensuring the stability of navigation data, thus reducing the risk of hardware damage.
Patent Information
- Application Number
- CN202511767152.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-11-28
- Publication Date
- 2025-12-26
AI Technical Summary
Existing drone navigation modules often use a single buffer structure, which makes it difficult to fully isolate vibrations of different frequencies, such as fuselage resonance, motor disturbances, and airflow impacts. This results in IMU attitude measurement being easily interfered with, positioning data experiencing jumps, and core perception accuracy being difficult to guarantee.
The design employs a combination of buffer components, air curtain components, and pretensioning components, including shock-absorbing springs, airbags, steel wire ropes, and air curtain generators. Through a complementary buffering system and passive sensing and active response, it achieves multi-media collaborative buffering, dynamically adapts to vibration frequencies, provides reverse damping and pretensioning fixation, and ensures the stability of the navigation module and servo motor.
It effectively isolates and attenuates the full-cycle vibration of the drone, protects the navigation module and servo motor, reduces the risk of hardware damage, and ensures the stability and accuracy of navigation data.
Smart Images
Figure CN121201432A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of unmanned aerial vehicles, in particular to an installation structure for unmanned aerial vehicle navigation and a rudder surface adjusting mechanism. BACKGROUND
[0002] The unmanned aerial vehicle navigation module is a core perception unit integrating IMU, GPS, Beidou positioning, and visual sensors, responsible for collecting flight position, attitude, speed, and other data and transmitting them to the flight control system to provide a basis for flight decision-making. The rudder surface is a deflectable control structure arranged on the wings and tail of the unmanned aerial vehicle, and the rudder is the only power source for driving the rudder surface to move as the power output end. The existing unmanned aerial vehicle navigation module installation mostly adopts a single buffer structure, lacks multi-medium collaborative buffer design, and is difficult to fully isolate vibrations of different frequencies such as body resonance, motor disturbance, and airflow impact, resulting in IMU attitude measurement being easily disturbed, positioning data jumping, and core perception accuracy being difficult to guarantee. SUMMARY
[0003] The present application aims to provide an installation structure for unmanned aerial vehicle navigation and a rudder surface adjusting mechanism to solve the problem of the existing unmanned aerial vehicle navigation module installation mostly adopting a single buffer structure, lacking multi-medium collaborative buffer design, and being difficult to fully isolate vibrations of different frequencies such as body resonance, motor disturbance, and airflow impact, resulting in IMU attitude measurement being easily disturbed, positioning data jumping, and core perception accuracy being difficult to guarantee.
[0004] To achieve the above-mentioned purpose, the present application provides the following technical solution: an installation structure for unmanned aerial vehicle navigation and a rudder surface adjusting mechanism, comprising an unmanned aerial vehicle, a navigation module, and a rudder, the inside of the unmanned aerial vehicle is provided with a buffer assembly, the inside of the unmanned aerial vehicle is provided with an air curtain assembly, and the inside of the unmanned aerial vehicle is provided with a pre-tightening assembly. The buffer assembly comprises a fixed block arranged inside the unmanned aerial vehicle, a steel wire rope arranged inside the fixed block, an air bag fixedly connected to one side of the outer surface of the fixed block, a bottom plate fixedly connected to one side of the outer surface of the fixed block, an air outlet arranged inside the air bag, and a throttle valve arranged inside the air outlet. The air curtain assembly comprises an air suction pump, a first air supply pipe arranged inside the air suction pump, a ring-shaped air curtain generator fixedly connected to one side of the outer surface of the bottom plate, the first air supply pipe being arranged inside the ring-shaped air curtain generator at the end away from the air suction pump, a second air supply pipe arranged inside the air suction pump, and the second air supply pipe being arranged inside the air bag at the end away from the air suction pump. The pre-tightening assembly includes multiple air cylinders, and slide rods are slidably embedded inside the multiple air cylinders in a horizontal direction. A push plate is fixedly connected to one side of the outer surface of each of the multiple slide rods. An air outlet pipe is provided inside the air bladder, and air guide pipes are provided inside the multiple air cylinders. The ends of the two sets of air guide pipes away from the air cylinders are located inside the air outlet pipes.
[0005] Preferably, multiple shock-absorbing springs are fixedly connected to one side of the outer surface of the drone, and the ends of the multiple shock-absorbing springs away from the drone are all fixedly connected to the base plate.
[0006] Preferably, a pressure valve is provided inside the air outlet pipe, and a connecting pipe is fixedly connected to the outer surface of the pressure valve. The interior of the connecting pipe is connected to the second air supply pipe.
[0007] Preferably, a return spring is fixedly connected to one side of the inner wall of the connecting pipe, and a plug is fixedly connected to the side of the return spring away from the connecting pipe, the plug being slidably embedded inside the connecting pipe in a vertical direction.
[0008] Preferably, a piston is fixedly connected to one side of the outer surface of each of the plurality of slide rods, and the plurality of pistons are horizontally slidably embedded inside the slide rods.
[0009] Preferably, the outer surfaces of the plurality of air cylinders are fixedly connected with connecting pipes, and two sets of baffles are fixedly connected to one side of the outer surface of the base plate.
[0010] Preferably, the plurality of air cylinders are fixedly connected to one side of the outer surface of the base plate, and the air pump is fixedly connected to one side of the outer surface of the base plate.
[0011] Compared with the prior art, the beneficial effects of the present invention are: 1. This invention utilizes a complementary composite buffer system formed by a shock-absorbing spring, an airbag, and a steel wire rope. This system overcomes the frequency limitations of a single buffer medium. The shock-absorbing spring, through its elastic deformation, bears the core static load while simultaneously buffering low- to medium-frequency vibrations such as fuselage resonance and motor idling, preventing rigid impacts from low-frequency vibrations on the buffer structure. The airbag, through the compression and expansion of its internal gas, quickly absorbs high-frequency micro-vibrations such as servo motor operating impacts and airflow disturbances, reducing the subtle impact of vibrations on the core components. The steel wire rope, utilizing its torsional deformation characteristics, provides reverse damping when the buffer structure is compressed, slowing down the compression rate. Meanwhile, its spiral structure can limit the lateral displacement and torsional offset of the base plate, avoiding structural skew during the buffering process. It covers the vibration types of the entire flight cycle of the UAV, achieving stable buffering at low frequencies and strong attenuation at high frequencies. When the UAV undergoes maneuvering flight or lateral vibration, the spiral tension of the steel wire rope can suppress the torsional deformation of the base plate, preventing the navigation module and the fixed block from torsional offset and ensuring the parallelism of the output shaft of the fixed block. At the same time, the rigidity of the steel wire rope can limit the maximum compression of the buffer structure, preventing the shock-absorbing spring from losing elasticity due to excessive compression and the airbag from rupturing due to over-range compression.
[0012] 2. This invention uses a throttle valve and a pressure valve to form a passive sensing and active response, achieving dynamic adaptation of buffering performance. When the vibration is small, the throttle valve opening is small, the airbag exhaust volume is limited, and the basic air pressure is maintained to ensure buffering flexibility and avoid excessive rigidity due to over-inflation. When the vibration amplitude increases, the airbag is compressed more, and the exhaust volume increases simultaneously. When the air pressure reaches the pressure valve threshold, the pressure valve opens and triggers the movement of the plug. The air pump continuously supplies air to the airbag through the second air delivery pipe, causing the airbag to expand rapidly and its rigidity to be significantly improved. It transforms from a flexible buffer into an auxiliary support, thereby working in conjunction with the steel wire rope and shock-absorbing spring to enhance the buffering effect.
[0013] 3. This invention is based on the air pressure triggering of the airbag to form a passive vibration lock. When the vibration amplitude reaches the threshold, the high-pressure gas after the pressure valve opens is introduced into the air cylinder. The thrust generated by the instantaneous injection of gas drives the push plate to squeeze the navigation module and the servo motor, realizing the pre-tightening and fixing of the core components. In the event of extreme vibration, such as collision or hard landing, the core components are quickly fixed to prevent them from violently shaking or shifting within the buffer structure. This effectively protects the internal components of the navigation module, the mounting interface of the servo motor and the connecting cables, and reduces the risk of hardware damage. Attached Figure Description
[0014] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the internal structure of the present invention; Figure 3 This is one of the partial structural schematic diagrams of the present invention; Figure 4 This is a schematic diagram of the wire rope structure of the present invention; Figure 5 This is a partial structural schematic diagram of the present invention; Figure 6 For the present invention Figure 5 Enlarged structural diagram at point A in the middle; Figure 7 For the present invention Figure 5 Enlarged structural diagram at point B; Figure 8 This is a partial structural schematic diagram of the present invention (third one). Figure 9 For the present invention Figure 8 Enlarged structural diagram at point C.
[0015] In the diagram: 1. Unmanned Aerial Vehicle (UAV); 101. Navigation Module; 102. Servo Motor; 2. Fixing Block; 201. Steel Wire Rope; 202. Base Plate; 3. Airbag; 301. Air Outlet; 302. Throttling Valve; 303. Air Outlet Pipe; 304. Pressure Valve; 4. Air Pump; 401. First Air Supply Pipe; 402. Annular Air Curtain Generator; 403. Second Air Supply Pipe; 404. Connecting Pipe; 5. Plug; 501. Return Spring; 6. Air Cylinder; 601. Sliding Rod; 602. Piston; 603. Connecting Pipe; 604. Air Guide Pipe; 7. Push Plate; 701. Baffle; 8. Shock Absorbing Spring. Detailed Implementation
[0016] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.
[0017] See Figures 1 to 9 As shown, the present invention provides an installation structure and control surface adjustment mechanism for unmanned aerial vehicle (UAV) navigation, including a UAV 1, a navigation module 101, and a servo motor 102. The UAV 1 has an internal buffer assembly, an internal air curtain assembly, and an internal pre-tensioning assembly. The buffer assembly includes a fixed block 2 inside the UAV 1, with a steel wire rope 201 inside the fixed block 2. An airbag 3 is fixedly connected to one side of the outer surface of the fixed block 2, and a base plate 202 is fixedly connected to one side of the outer surface of the fixed block 2. An air outlet 301 is provided inside the air outlet 301, and a throttle valve 302 is provided inside the air outlet 301. Multiple shock-absorbing springs 8 are fixedly connected to one side of the outer surface of the UAV 1, and the ends of the multiple shock-absorbing springs 8 furthest from the UAV 1 are all fixedly connected to the base plate 202. See Figures 1 to 5 As shown, after the navigation module 101 and servo motor 102 are installed in the base plate 202 inside the UAV 1, the navigation module 101 provides navigation for the UAV, and the servo motor 102 adjusts the control surfaces of the UAV. When the UAV 1 generates lateral force during flight, the lateral traction force is provided by the twisted and braided steel wire rope 201. At the same time, when vibration or shaking occurs during flight, the shock-absorbing spring 8 and airbag 3 provide buffering. Through the above technical solution, the shock-absorbing spring 8, airbag 3 and steel wire rope 201 form a complementary composite buffering system, breaking through the frequency limitation of a single buffering medium. The shock-absorbing spring 8 bears the core static load by elastic deformation, while buffering low-frequency vibrations such as fuselage resonance and motor idling, avoiding rigid impact from low-frequency vibrations in the buffering structure. The airbag 3 quickly absorbs the servo motor 101 through the compression and expansion of the internal gas. 2. High-frequency micro-vibrations such as working impacts and airflow disturbances reduce the subtle impact of vibrations on core components. The steel wire rope 201 utilizes its torsional deformation characteristics to provide reverse damping when the buffer structure is compressed, slowing down the compression rate. At the same time, its helical structure can limit the lateral displacement and torsional offset of the base plate 202, avoiding structural skewing during the buffering process. It covers the vibration types of the entire flight cycle of the UAV 1, achieving stable buffering at low frequencies and strong attenuation at high frequencies. When the UAV 1 undergoes maneuvering flight or lateral vibration, the helical tension of the steel wire rope 201 can suppress the torsional deformation of the base plate 202, preventing torsional offset between the navigation module 101 and the fixed block 2, ensuring the parallelism of the output shaft of the fixed block 2. At the same time, the rigidity of the steel wire rope 201 can limit the maximum compression of the buffer structure, preventing the shock-absorbing spring 8 from losing elasticity due to excessive compression and the airbag 3 from rupturing due to over-extension. The air curtain assembly includes a vacuum pump 4, and a first air supply pipe 401 is provided inside the vacuum pump 4. An annular air curtain generator 402 is fixedly connected to one side of the outer surface of the base plate 202. The end of the first air supply pipe 401 away from the vacuum pump 4 is located inside the annular air curtain generator 402. A second air supply pipe 403 is provided inside the vacuum pump 4, and the end of the second air supply pipe 403 away from the vacuum pump 4 is located inside the airbag 3. A pressure valve 304 is provided inside the air outlet pipe 303. A connecting pipe 404 is fixedly connected to the outer surface of the pressure valve 304. The interior of the connecting pipe 404 is connected to the second air supply pipe 403. A return spring 501 is fixedly connected to one side of the inner wall of the connecting pipe 404, and a plug 5 is fixedly connected to the side of the return spring 501 away from the connecting pipe 404. The plug 5 is slidably embedded in the interior of the connecting pipe 404 in a vertical direction. See Figures 2 to 9As shown, during the flight of the UAV 1, the air pump 4 is activated, and the air pump 4 continuously supplies air to the annular air curtain generator 402 through the first air supply pipe 401. The annular air curtain generator 402 forms an annular air curtain, which forms a barrier on the sensor surface of the navigation module 101, preventing foreign objects such as dust, raindrops, and insects from adhering, avoiding signal obstruction or image blurring, and ensuring the stability of navigation data acquisition. At the same time, the air curtain airflow can directly act on the outer shell of the fixed block 2, accelerating heat dissipation. When vibration occurs, if the vibration amplitude is small, the weak airflow in the airbag 3 flows out through the throttle valve 302. If the vibration amplitude is large, the airflow is controlled by the throttle valve 302. At this time, the pressure in the airbag 3 exceeds the threshold of the pressure valve 304 in the air outlet pipe 303, and the gas is delivered to the connecting pipe 404 through the air outlet pipe 303. The gas pushes the plug 5 to slide in the connecting pipe 404, and the plug... The plug 5 squeezes the reset spring 501, thereby opening the second air supply pipe 403. At this time, the plug 5 no longer blocks the air pump 4 from supplying gas to the airbag 3 through the second air supply pipe 403. Through the above technical solution, the throttle valve 302 and the pressure valve 304 form a passive sensing and active response, realizing dynamic adaptation of the buffer performance. When the vibration is small, the throttle valve 302 opens less, the airbag 3 has a limited exhaust volume, and the basic air pressure is maintained to ensure the buffer flexibility and avoid excessive buffer rigidity due to over-inflation. When the vibration amplitude increases, the airbag 3 is squeezed more, and the exhaust volume increases simultaneously. When the air pressure reaches the threshold of the pressure valve 304, the pressure valve 304 opens and triggers the plug 5 to move. The air pump 4 continuously supplies air to the airbag 3 through the second air supply pipe 403, causing the airbag 3 to expand rapidly and its rigidity to be significantly improved. It transforms from a flexible buffer to an auxiliary support, thereby working together with the wire rope 201 and the shock-absorbing spring 8 to enhance the buffer effect.
[0018] The pre-tightening assembly includes multiple air cylinders 6, and slide rods 601 are horizontally slidably embedded inside the multiple air cylinders 6. Push plates 7 are fixedly connected to one side of the outer surface of each of the multiple slide rods 601. An air outlet pipe 303 is provided inside the air bag 3. An air guide pipe 604 is provided inside the multiple air cylinders 6, and the ends of the two sets of air guide pipes 604 away from the air cylinders 6 are located inside the air outlet pipe 303. A piston 602 is fixedly connected to one side of the outer surface of each of the multiple slide rods 601, and the multiple pistons 602 are horizontally slidably embedded inside the slide rods 601. A piston 602 is fixedly connected to one side of the outer surface of each of the multiple slide rods 601, and the multiple pistons 602 are horizontally slidably embedded inside the slide rods 601. Multiple air cylinders 6 are fixedly connected to one side of the outer surface of the base plate 202, and a vacuum pump 4 is fixedly connected to one side of the outer surface of the base plate 202. See Figures 2 to 8As shown, when the vibration amplitude is large, after the gas breaks through the pressure valve 304, the gas is delivered to multiple air cylinders 6 through the air guide pipe 604. The multiple air cylinders 6 are connected by the connecting pipe 603 to balance the air pressure in the air cylinders on both sides. The injection of gas pushes the piston 602 in the air cylinder 6 to move. The piston 602 pushes the slide rod 601 to move, and the slide rod 601 pushes the push plate 7 to move. The push plate 7 is made of a hard inner and soft outer material. The push plate 7 contacts the navigation module 101 and the servo motor 102, thereby fixing the navigation module 101 and the servo motor 102 between the push plate 7 and the baffle 701. Thus, when the vibration amplitude is large, it can effectively control the vibration. The navigation module 101 and servo motor 102 are pre-tightened. Through the above technical solution, the air pressure of the airbag 3 is used as a premise to form a passive vibration lock. When the vibration amplitude reaches the threshold, the high-pressure gas after the pressure valve 304 is opened is introduced into the air cylinder 6. The thrust generated by the instantaneous injection of gas drives the push plate 7 to squeeze the navigation module 101 and servo motor 102, thereby achieving the pre-tightening and fixing of the core components. In the event of extreme vibration, such as collision or hard landing, the core components are quickly fixed to prevent them from violently shaking or shifting within the buffer structure. This effectively protects the internal components of the navigation module 101, the installation interface of the servo motor 102 and the connecting cables, and reduces the risk of hardware damage.
[0019] Working principle: After the navigation module 101 and servo motor 102 are installed in the base plate 202 inside the UAV 1, the navigation module 101 provides navigation for the UAV, and the servo motor 102 adjusts the control surfaces of the UAV. When the UAV 1 generates lateral force during flight, the steel wire rope 201 with a winding and braided arrangement provides lateral traction force. At the same time, when vibration or shaking occurs during flight, the shock-absorbing spring 8 and airbag 3 provide buffering.
[0020] During flight, the UAV 1 activates the air pump 4, which continuously supplies air to the annular air curtain generator 402 via the first air supply pipe 401. This forms an annular air curtain, which acts as a barrier on the sensor surface of the navigation module 101, preventing dust, raindrops, insects, and other foreign objects from adhering, thus avoiding signal obstruction or blurred imaging and ensuring the stability of navigation data acquisition. Simultaneously, the airflow from the air curtain can directly act on the outer shell of the fixed block 2, accelerating heat dissipation. When vibration occurs, if the vibration amplitude is small, the air... The weak airflow inside the airbag 3 flows out through the throttle valve 302. When the vibration amplitude is large, the outflow of airflow is controlled by the throttle valve 302. At this time, the pressure inside the airbag 3 exceeds the threshold of the pressure valve 304 in the air outlet pipe 303. The gas is delivered to the connecting pipe 404 through the air outlet pipe 303. The gas pushes the plug 5 to slide in the connecting pipe 404. The plug 5 squeezes the reset spring 501, thereby opening the second air delivery pipe 403. At this time, the plug 5 no longer blocks the gas delivered by the suction pump 4 to the inside of the airbag 3 through the second air delivery pipe 403.
[0021] When the vibration amplitude is large, the gas breaks through the pressure valve 304 and is then transported to multiple air cylinders 6 through the air guide pipe 604. The multiple air cylinders 6 are connected by the connecting pipe 603 to balance the air pressure in the air cylinders on both sides. The injection of gas pushes the piston 602 in the air cylinder 6 to move. The piston 602 pushes the slide rod 601 to move, and the slide rod 601 pushes the push plate 7 to move. The push plate 7 is made of a hard inner and soft outer material. The push plate 7 contacts the navigation module 101 and the servo motor 102, thereby fixing the navigation module 101 and the servo motor 102 between the push plate 7 and the baffle 701. This pre-tightens the navigation module 101 and the servo motor 102 when the vibration amplitude is large.
[0022] Although embodiments of the 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 invention, the scope of which is defined by the appended claims and their equivalents.
Claims
1. An installation structure and control surface adjustment mechanism for unmanned aerial vehicle (UAV) navigation, comprising a UAV (1), a navigation module (101), and a servo motor (102), characterized in that, The drone (1) is equipped with a buffer component, an air curtain component, and a pre-tightening component. The buffer assembly includes a fixed block (2) disposed inside the drone (1), and a steel wire rope (201) is disposed inside the fixed block (2). An airbag (3) is fixedly connected to one side of the outer surface of the fixed block (2), and a base plate (202) is fixedly connected to one side of the outer surface of the fixed block (2). An air outlet (301) is disposed inside the air outlet (301), and a throttle valve (302) is disposed inside the air outlet (301). The air curtain assembly includes an air pump (4), and the air pump (4) is provided with a first air supply pipe (401). An annular air curtain generator (402) is fixedly connected to one side of the outer surface of the base plate (202). The end of the first air supply pipe (401) away from the air pump (4) is located inside the annular air curtain generator (402). The air pump (4) is provided with a second air supply pipe (403), and the end of the second air supply pipe (403) away from the air pump (4) is located inside the airbag (3). The pre-tightening assembly includes multiple air cylinders (6), and slide rods (601) are slidably embedded inside the multiple air cylinders (6) in a horizontal direction. Push plates (7) are fixedly connected to one side of the outer surface of each of the multiple slide rods (601). An air outlet pipe (303) is provided inside the air bag (3). An air guide pipe (604) is provided inside the multiple air cylinders (6), and the ends of the two sets of air guide pipes (604) away from the air cylinders (6) are both located inside the air outlet pipe (303).
2. The mounting structure and control surface adjustment mechanism for UAV navigation according to claim 1, characterized in that, Multiple shock-absorbing springs (8) are fixedly connected to one side of the outer surface of the drone (1), and the ends of the multiple shock-absorbing springs (8) away from the drone (1) are fixedly connected to the base plate (202).
3. The mounting structure and control surface adjustment mechanism for UAV navigation according to claim 1, characterized in that, The air outlet pipe (303) is equipped with a pressure valve (304) inside. A connecting pipe (404) is fixedly connected to the outer surface of the pressure valve (304). The interior of the connecting pipe (404) is connected to the second air supply pipe (403).
4. The mounting structure and control surface adjustment mechanism for UAV navigation according to claim 3, characterized in that, A return spring (501) is fixedly connected to one side of the inner wall of the connecting pipe (404), and a plug (5) is fixedly connected to the side of the return spring (501) away from the connecting pipe (404). The plug (5) is slidably embedded in the interior of the connecting pipe (404) in a vertical direction.
5. The mounting structure and control surface adjustment mechanism for UAV navigation according to claim 1, characterized in that, A piston (602) is fixedly connected to one side of the outer surface of each of the multiple slide rods (601), and the multiple pistons (602) are all horizontally slidably embedded inside the slide rods (601).
6. The mounting structure and control surface adjustment mechanism for UAV navigation according to claim 1, characterized in that, The outer surfaces of the multiple air cylinders (6) are fixedly connected with connecting pipes (603), and two sets of baffles (701) are fixedly connected to one side of the outer surface of the base plate (202).
7. The mounting structure and control surface adjustment mechanism for UAV navigation according to claim 1, characterized in that, Multiple air cylinders (6) are fixedly connected to one side of the outer surface of the base plate (202), and the air pump (4) is fixedly connected to one side of the outer surface of the base plate (202).