Cross-medium sea-air dual-purpose unmanned aerial vehicle floating control device

Abstract

The utility model discloses a cross-medium sea-air dual-purpose unmanned aerial vehicle floating control device which comprises a shell, a gas-liquid storage cabin, a peristaltic pump, a control mechanism and a power supply mechanism, and the gas-liquid storage cabin is installed on the shell; the peristaltic pump is connected with the shell through the mounting assembly; the gas-liquid storage cabin is connected with the control mechanism through a first connecting pipe, and the peristaltic pump is connected with the control mechanism through a second connecting pipe; the power supply mechanism is used for supplying power to the peristaltic pump and the control mechanism. The gas-liquid storage cabin, the peristaltic pump, the control mechanism and the power supply mechanism are arranged in the aircraft, water is conveyed and drained into the gas-liquid storage cabin through the peristaltic pump, and the proportion of air to water in the gas-liquid storage cabin is changed, so that the aircraft can be reliably and continuously switched between a water medium and an air medium; the peristaltic pump is controlled to continuously carry out water delivery and drainage operation on the gas-liquid storage cabin, and at the moment, the effect of accurately controlling the diving depth of the aircraft in water can be achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a floating control device for a cross-medium sea-air dual-purpose unmanned aircraft. Background Art

[0002] A cross-media dual-purpose sea and air unmanned aerial vehicle is a vehicle that can adaptively achieve motion transition and continuous existence between two different fluid media, water and air, and can autonomously navigate continuously and perform specific tasks in both media. The rotor-type cross-media dual-purpose sea and air unmanned aerial vehicle has become an important research direction of cross-media unmanned aerial vehicles due to its flexibility and no restrictions on take-off and landing sites.

[0003] In the prior art, a floating control mechanism is required for a cross-media dual-purpose sea-air unmanned aerial vehicle to accurately determine its underwater depth and assist its power system in achieving a cross-media process transition. At present, how to achieve reliable and continuous switching of the cross-media unmanned aerial vehicle between the water and air media and accurately control the diving depth is a key issue of the floating control mechanism of the cross-media unmanned aerial vehicle. In this regard, the present application proposes a floating control device for a cross-media dual-purpose sea-air unmanned aerial vehicle to solve such problems. Utility Model Content

[0004] Based on this, in order to solve the problems existing in the prior art, the present application provides a floating control device for a cross-medium sea-air dual-purpose unmanned aerial vehicle, including a shell, a gas-liquid storage cabin, a peristaltic pump, a control mechanism and a power supply mechanism, wherein the gas-liquid storage cabin is installed on the shell;

[0005] The peristaltic pump is connected to the housing through a mounting assembly;

[0006] The gas-liquid storage chamber is connected to the control mechanism through a first connecting pipe, the peristaltic pump is connected to the control mechanism through a second connecting pipe, and the first connecting pipe and the second connecting pipe are in communication through the control mechanism;

[0007] The power supply mechanism is used to supply energy to the peristaltic pump and the control mechanism;

[0008] The peristaltic pump continuously delivers water to and discharges water from the gas-liquid storage chamber, thereby changing the ratio of air and water in the gas-liquid storage chamber.

[0009] Furthermore, the installation assembly includes a fixing ring, a hanging ear and a support frame. The peristaltic pump is fixedly mounted in the fixing ring. At least two hanging ears are arranged on the fixing ring. Each hanging ear is correspondingly provided with a support frame. One end of the support frame is detachably connected to the hanging ear, and the other end of the support frame is fixedly connected to the shell.

[0010] Furthermore, the control mechanism includes a voltage stabilizing module, a control module and an electromagnetic water valve. The voltage stabilizing module and the control module are detachably connected to the shell, and the electromagnetic water valve is fixedly installed on the shell. The voltage stabilizing module is electrically connected to the control module and the peristaltic pump respectively, and the control module is electrically connected to the electromagnetic water valve. The first connecting pipe and the second connecting pipe are connected to the electromagnetic water valve.

[0011] Furthermore, fasteners are provided at the connection points between the first connecting pipe, the second connecting pipe and the electromagnetic water valve.

[0012] Furthermore, the power supply mechanism includes a high energy density lithium battery, which is detachably mounted on the housing via a fixing member, and the high energy density lithium battery is electrically connected to the voltage stabilizing module.

[0013] Furthermore, the first connecting pipe and the second connecting pipe are both hoses.

[0014] Beneficial effects: By arranging a gas-liquid storage cabin, a peristaltic pump, a control mechanism and a power supply mechanism inside the aircraft, and controlling the peristaltic pump to supply water to and drain water from the gas-liquid storage cabin, the ratio of air and water in the gas-liquid storage cabin is changed, so that the aircraft can reliably and continuously switch between the water-air medium. By controlling the peristaltic pump to continuously supply water to and drain water from the gas-liquid storage cabin, the effect of accurately controlling the diving depth of the aircraft in the water can be achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0016] Figure 1 It is a three-dimensional structural schematic diagram of the utility model cross-medium sea-air dual-purpose unmanned aerial vehicle floating control device;

[0017] Figure 2 It is a schematic diagram of the planar structure of the floating control device for a cross-medium dual-purpose sea and air unmanned aerial vehicle of the utility model;

[0018] Figure 3 for Figure 2 Enlarged view of point A in the middle;

[0019] Figure 4 for Figure 2 Enlarged view of point B in the middle;

[0020] In the figure: 1. Shell; 2. Gas-liquid storage compartment; 3. Peristaltic pump; 31. Fixing ring; 32. Hanging ear; 33. Support frame; 4. Control mechanism; 41. Voltage stabilizing module; 42. Control module; 43. Solenoid water valve; 5. Power supply mechanism; 51. Battery; 52. Fixing piece; 6. First connecting pipe; 7. Second connecting pipe; 8. Fastener.

[0021] The realization of the purpose, functional features and advantages of the utility model will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0023] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back...) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0024] In addition, the descriptions of "first", "second", etc. in the present utility model are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, "and / or" in the full text includes three solutions. Taking A and / or B as an example, it includes technical solution A, technical solution B, and technical solution that satisfies both A and B; in addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present utility model.

[0025] like Figure 1-2 As shown, the embodiment of the present application provides a floating control device for a cross-medium sea-air dual-purpose unmanned aerial vehicle, including a shell 1, a gas-liquid storage cabin 2, a peristaltic pump 3, a control mechanism 4 and a power supply mechanism 5, wherein the gas-liquid storage cabin 2 is installed on the shell 1;

[0026] The peristaltic pump 3 is connected to the housing 1 through a mounting assembly;

[0027] The gas-liquid storage chamber 2 is connected to the control mechanism 4 via a first connecting pipe 6, the peristaltic pump 3 is connected to the control mechanism 4 via a second connecting pipe 7, and the first connecting pipe and the second connecting pipe are in communication via the control mechanism;

[0028] The power supply mechanism 5 is used to supply energy to the peristaltic pump 3 and the control mechanism 4;

[0029] The peristaltic pump 3 continuously delivers water to and drains water from the gas-liquid storage chamber 2, changing the volume ratio of air and water in the gas-liquid storage chamber 2, thereby controlling the aircraft to float or sink.

[0030] In this embodiment, the housing 1 refers to the outer shell of the aircraft, and preferably, the gas-liquid storage cabin 2, the peristaltic pump 3, the control mechanism 4 and the power supply mechanism 5 are all installed on the inner wall of the housing 1, and the gas-liquid storage cabin 2 is fastened to the housing 1 by nuts;

[0031] It should also be noted that the peristaltic pump 3 in the present application is individually controlled by the onboard equipment system of the aircraft;

[0032] The peristaltic pump 3 generates fluid flow by compressing a flexible pipe (usually a hose or a pipe) rather than rotating mechanical parts. This design gives the peristaltic pump 3 some unique advantages, such as: no pollution, wide applicability, and controllable flow rate; the most important of which is that the flow rate of the fluid can be easily adjusted by changing the pressure of the compressed pipe or rotating the speed of the peristaltic pump 3.

[0033] When the aircraft is flying in the air, the peristaltic pump 3 and the control mechanism 4 do not work, and the inside of the gas-liquid storage cabin 2 is full of air; when the aircraft is in the water, the peristaltic pump 3 is driven by the onboard equipment system to input water into the gas-liquid storage cabin 2. At this time, the proportion of air in the gas-liquid storage cabin 2 gradually decreases, which will gradually increase the weight of the aircraft, thereby causing the aircraft to sink. The peristaltic pump 3 is driven by the onboard equipment system to drain the gas-liquid storage cabin 2 to the outside. At this time, the proportion of water in the gas-liquid storage cabin 2 gradually decreases, which will gradually reduce the weight of the aircraft, thereby causing the aircraft to float;

[0034] The peristaltic pump 3 is controlled by the onboard equipment system to continuously deliver water to and drain water from the gas-liquid storage compartment 2, so that the diving depth of the aircraft in the water can be precisely controlled.

[0035] In one embodiment, the control mechanism 4 includes a voltage stabilizing module 41, a control module 42 and an electromagnetic water valve 43. The voltage stabilizing module 41 and the control module 42 are detachably connected to the shell 1, and the electromagnetic water valve 43 is fixedly installed on the shell 1. The voltage stabilizing module 41 is electrically connected to the control module 42 and the peristaltic pump 3 respectively, the control module 42 is electrically connected to the electromagnetic water valve 43, and the first connecting pipe 6 is connected to the second connecting pipe 7 through the electromagnetic water valve 43.

[0036] In this embodiment, the voltage stabilizing module 41 and the control module 42 are fixedly connected to the housing 1 through nuts. The voltage stabilizing module 41 can provide a stable voltage to the control module 42 and the peristaltic pump 3 to ensure the stable voltage supply required for the normal operation of the control module 42 and the peristaltic pump 3. The control module 42 can control the opening and closing of the electromagnetic water valve 43.

[0037] Specifically, when the control module 42 receives a diving instruction, the peristaltic pump 3 is started through the airborne equipment system, and the electromagnetic water valve 43 is opened through the control module, and the peristaltic pump 3 will transport the external water into the gas-liquid storage compartment 2. When the control module 42 receives a floating instruction, the airborne equipment system controls the peristaltic pump 3 to discharge the water inside the gas-liquid storage compartment 2. When the desired diving depth is adjusted, the peristaltic pump 3 and the electromagnetic water valve 43 are closed to keep the aircraft at the diving depth.

[0038] Preferably, the electromagnetic water valve 43 is of DC 12V normally closed type.

[0039] In one embodiment, the power supply mechanism 5 includes a high energy density lithium battery 51 , which is detachably mounted on the housing 1 via a fixing member 52 , and the high energy density lithium battery 51 is electrically connected to the voltage stabilizing module 41 .

[0040] In this embodiment, the high energy density lithium battery 51 refers to a lithium ion battery 51 that can store more electrical energy in a smaller volume and weight. The high energy density lithium battery 51 can provide the aircraft with a longer cruising range and a more lasting use time. The fixing part 52 is fixedly connected to the shell 1 by a nut.

[0041] In one embodiment, the first connecting pipe 6 and the second connecting pipe 7 are both hoses.

[0042] like Figure 3 As shown, in one embodiment, the mounting assembly includes a fixing ring 31, a hanging ear 32 and a support frame 33. The peristaltic pump 3 is fixedly mounted in the fixing ring 31. At least two hanging ears 32 are arranged on the fixing ring 31. Each hanging ear 32 is correspondingly provided with a support frame 33. One end of the support frame 33 is detachably connected to the hanging ear 32, and the other end of the support frame 33 is fixedly connected to the shell 1.

[0043] In this embodiment, during installation, the fixing ring 31 is sleeved on the outer surface of the peristaltic pump 3, and then the hanging ears 32 are fixedly connected to the corresponding support frame 33 with nuts;

[0044] Preferably, the number of the hanging ears 32 and the number of the supporting frames 33 are both two, and they are located at symmetrical positions on both sides of the fixing ring 31 respectively.

[0045] like Figure 4As shown, in one embodiment, fasteners 8 are provided at the connection points between the first connecting pipe 6 , the second connecting pipe 7 and the electromagnetic water valve 43 .

[0046] In this embodiment, fasteners 8 are provided at the connection points between the first connecting pipe 6, the second connecting pipe 7 and the electromagnetic water valve 43, in order to enhance the sealing performance of the connection points between the first connecting pipe 6, the second connecting pipe 7 and the electromagnetic water valve 43, and prevent water leakage from affecting the internal voltage stabilizing module 41, the control module 42 and the power supply mechanism 5;

[0047] The fastener 8 is a pipe clamp.

[0048] The working principle of a floating control device for a cross-medium sea-air dual-purpose unmanned aerial vehicle is as follows:

[0049] When the cross-medium sea-air UAV stalls and lands at sea level, the airborne equipment system outputs voltage to the electromagnetic water valve 43 through the control module 42 to make the electromagnetic water valve 43 in a normally open state, and at the same time, the airborne equipment system controls the peristaltic pump 3 to extract water from the external environment through the first connecting pipe 6 and the second connecting pipe 7 into the gas-liquid storage cabin 2 to change the weight (discharge volume) of the cross-medium sea-air dual-purpose unmanned aerial vehicle until the cross-medium sea-air dual-purpose unmanned aerial vehicle is completely immersed; when it is necessary to adjust the diving depth, the airborne equipment system can control the peristaltic pump 3 to continuously supply water to and drain water from the gas-liquid storage cabin 2, and at this time, the diving depth of the aircraft in the water can be accurately controlled; after the adjustment is completed, the airborne equipment system does not output voltage to the electromagnetic water valve through the control module 42 to make the electromagnetic water valve in a normally closed state, and at the same time, the airborne equipment system controls the peristaltic pump 3 to be in a stopped state and not to pump or release water;

[0050] The airborne equipment system outputs voltage to the electromagnetic water valve 43 through the control module 42, so that the electromagnetic water valve 43 is in a normally open state. At the same time, the airborne equipment system controls the peristaltic pump 3 to reverse the output and extract water from the gas-liquid storage tank and discharge it into the external environment through a hose until there is no water in the gas-liquid storage tank, thereby changing the weight (discharge volume) of the cross-media sea-and-air dual-purpose unmanned aerial vehicle so that the cross-media sea-and-air dual-purpose unmanned aerial vehicle's buoyancy auxiliary vector tilting power system completes the water discharge process. After that, the airborne equipment system does not output voltage to the electromagnetic water valve 43 through the control module 42, so that the electromagnetic water valve 43 is in a normally closed state. At the same time, the airborne equipment system controls the peristaltic pump 3 to be in a stopped state and does not pump or release water.

[0051] The above description is only a preferred embodiment of the utility model, and does not limit the patent scope of the utility model. All equivalent structural changes made by using the contents of the utility model specification and drawings under the utility model concept, or directly / indirectly used in other related technical fields are included in the patent protection scope of the utility model.

Claims

1. A floating control device for a cross-medium sea-air dual-purpose unmanned aerial vehicle, characterized in that: include: A shell, a gas-liquid storage chamber, a peristaltic pump, a control mechanism and a power supply mechanism, wherein the gas-liquid storage chamber is installed on the shell; The peristaltic pump is connected to the housing via a mounting assembly; The gas-liquid storage chamber is connected to the control mechanism via a first connecting pipe, the peristaltic pump is connected to the control mechanism via a second connecting pipe, and the first connecting pipe and the second connecting pipe are in communication with each other via the control mechanism; The power supply mechanism is used to supply energy to the peristaltic pump and the control mechanism; The peristaltic pump continuously delivers water to and discharges water from the gas-liquid storage chamber, thereby changing the ratio of air and water in the gas-liquid storage chamber.

2. The cross-medium sea-air dual-purpose unmanned aerial vehicle floating control device according to claim 1 is characterized in that: The mounting assembly includes a fixing ring, a hanging ear and a support frame. The peristaltic pump is fixedly sleeved in the fixing ring. At least two hanging ears are arranged on the fixing ring. Each of the hanging ears is correspondingly provided with the support frame. One end of the support frame is detachably connected to the hanging ear, and the other end of the support frame is fixedly connected to the shell.

3. The cross-medium sea-air dual-purpose unmanned aerial vehicle floating control device according to claim 1 is characterized in that: The control mechanism includes a voltage stabilizing module, a control module and an electromagnetic water valve. The voltage stabilizing module and the control module are detachably connected to the shell, and the electromagnetic water valve is fixedly installed on the shell. The voltage stabilizing module is electrically connected to the control module and the peristaltic pump respectively, and the control module is electrically connected to the electromagnetic water valve. The first connecting pipe and the second connecting pipe are connected to the electromagnetic water valve.

4. The floating control device for a cross-medium dual-purpose sea and air unmanned aerial vehicle according to claim 3 is characterized in that: Fasteners are provided at the connection points between the first connecting pipe, the second connecting pipe and the electromagnetic water valve.

5. The floating control device for a cross-medium dual-purpose sea and air unmanned aerial vehicle according to claim 3 is characterized in that: The power supply mechanism comprises a high energy density lithium battery and a fixing part. The high energy density lithium battery is detachably mounted on the housing through the fixing part. The high energy density lithium battery is electrically connected to the voltage stabilizing module.

6. The cross-medium sea-air dual-purpose unmanned aerial vehicle floating control device according to claim 1 is characterized in that: The first connecting pipe and the second connecting pipe are both hoses.

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