Aircraft body and underwater unmanned aircraft

Abstract

The invention belongs to the field of tools specially suitable for underwater operation, and particularly relates to an aircraft body and an underwater unmanned aircraft. In order to prevent the unmanned aerial vehicle from being in contact with sea waves during release and recovery, the invention provides an aircraft body. The aircraft body comprises a storage bin with a hatch cover, an air jet opening, a control unit, a high-pressure air source and an air jet channel communicating the high-pressure air source with the air jet opening are arranged on the aircraft body, an air jet valve is arranged at the air jet channel and / or the air jet opening, and the air jet valve has an opening state used for enabling high-pressure air to be jetted out of the air jet opening so that the hatch cover can be higher than the water surface. The control unit is used for controlling the hatch cover to be opened when the air injection valve is in the open state and sequentially controlling the hatch cover and the air injection valve to be closed after the unmanned aerial vehicle is released or recycled. The invention also provides an underwater unmanned vehicle comprising the vehicle body. The hatch cover is higher than the water surface through high-pressure airflow, then the hatch cover is controlled to be opened to release or recover the unmanned aerial vehicle, and therefore the unmanned aerial vehicle is prevented from making contact with seawater.

Description

Technical Field

[0001] The invention belongs to the field of tools specially suitable for underwater operations, and in particular relates to a vehicle body and an underwater unmanned vehicle. Background Art

[0002] When conducting maritime rescue, underwater unmanned vehicles are needed to detect underwater information, while rescuers on ships use cameras to observe surface information. In actual rescue, due to the large area to be searched, multiple ships are often required, wasting manpower and resources.

[0003] To overcome the above problems, new underwater unmanned vehicles are equipped with drones. When operating, the drone searches on the water surface while the underwater unmanned vehicle searches underwater simultaneously. At this time, only a few ships and multiple new underwater unmanned vehicles are needed to complete the search, saving manpower and material resources.

[0004] For example, a Chinese invention patent application with an application publication date of 2020.12.11 and application publication number CN112061354A discloses an autonomous underwater vehicle that can carry and recover a drone. The underwater vehicle is equipped with a drone, and when the underwater vehicle floats to the surface, the drone can be released or recovered.

[0005] However, in the above-mentioned underwater vehicle, when releasing or recovering the drone, the waves will affect the posture of the underwater vehicle, causing the drone to contact with seawater, which will lead to failure in releasing the drone and damage to the drone.

[0006] To solve the above problems, a Chinese invention patent with authorization announcement number CN113212713B and authorization announcement date 2022.07.05 discloses an underwater vehicle that supports vertical launch. The underwater vehicle (equivalent to the vehicle body) is equipped with a drone. Specifically, the underwater vehicle includes a storage bin, and the drone is carried in the storage bin. The storage bin has a hatch that can be opened and closed. An airbag is provided at the front end of the underwater vehicle, and the hatch is arranged at the front end of the underwater vehicle. When the hatch is opened, a launch port for the drone to pass through is formed.

[0007] When releasing the drone, a high-pressure gas cylinder is used to inflate the airbag, causing it to expand. After the airbag expands, the underwater vehicle is in a vertical state due to the action of buoyancy; then, the propeller at the tail of the underwater vehicle is started, causing the launch port to move above the water surface; finally, the drone can be launched through the launch port.

[0008] The above invention patent does not disclose whether the airbag is deflated, so there are two situations. First, the airbag is not deflated, and the staff drives the ship to salvage the underwater vehicle. At this time, the underwater vehicle can no longer continue the search work; second, the airbag is deflated. At this time, it is necessary to ensure that the gas in the airbag is discharged cleanly and to ensure that seawater does not enter the airbag. The above invention patent does not disclose the structure related to the above content. Summary of the invention

[0009] The purpose of the present invention is to provide an aircraft body to solve the technical problem that sea waves affect the release of drones.

[0010] The present invention also aims to provide an underwater unmanned vehicle to solve the same technical problems mentioned above.

[0011] In order to achieve the above-mentioned purpose, the technical solution of the aircraft body provided by the present invention is: A vehicle body comprises a storage bin for carrying an unmanned aerial vehicle, the storage bin having an openable hatch cover, a jet port, a control unit, a high-pressure gas source storing high-pressure gas, and a jet channel connecting the high-pressure gas source and the jet port are provided on the vehicle body, a jet valve is provided at the jet channel and / or the jet port, the control unit is used to control the opening and closing of the jet valve, the jet valve has a closed state and an open state for allowing high-pressure gas to be ejected from the jet port so that the hatch cover is above the water surface, the control unit is used to control the hatch cover to open when the jet valve is in the open state, and to control the hatch cover and the jet valve to close in sequence after the unmanned aerial vehicle is released or recovered.

[0012] Furthermore, jet wings are provided on both sides of the aircraft body, and the jet ports are located at the tail ends of the jet wings.

[0013] Furthermore, a storage cabin is provided on the aircraft body, and the jet wing has a stowed state in which it is located inside the storage cabin to reduce the resistance encountered by the aircraft body when sailing underwater, and an expanded state outside the storage cabin. The control unit is used to control the opening of the jet valve when the jet wing is in the expanded state.

[0014] Furthermore, the jet port and the hatch are both located at the head of the vehicle body.

[0015] Furthermore, the direction of the jet port is perpendicular to the axial direction of the aircraft body.

[0016] Furthermore, the high-pressure gas source is a high-pressure gas tank detachably installed in a storage bin.

[0017] Furthermore, a launching device for launching the UAV is provided in the storage compartment.

[0018] Furthermore, the ejection device includes an ejection seat for launching the UAV, a compression elastic member is provided between the bottom wall of the storage bin and the ejection seat, a telescopic mechanism is also provided in the storage bin, a slot for inserting the telescopic mechanism is provided on the ejection seat, the telescopic mechanism has a longer state in which the compression elastic member is inserted into the slot when the compression elastic member is compressed, and a shorter state in which the telescopic mechanism is not inserted into the slot; the control unit is used to control the telescopic mechanism to switch from a longer state to a shorter state, so that the compression elastic member is reset and the UAV is ejected.

[0019] Furthermore, the hatch cover is located on the outer peripheral surface of the aircraft body, and the hatch cover and the jet port are respectively located on opposite sides of the aircraft body.

[0020] The beneficial effects of the aircraft body of the present invention are as follows: the present invention is an improved invention. In the present invention, the aircraft body is provided with an air jet, an air jet valve and a high-pressure gas source. When in use, the drone can be carried in the storage bin and the aircraft body can be used to transport the drone to the area to be searched.

[0021] During the release of the drone, the control unit controls the jet valve to be in the open state, and high-pressure gas is ejected from the jet port, thereby providing an upward force to the aircraft body to keep the hatch above the water surface; then, the control unit controls the hatch to open, so that the drone can be released from the storage compartment; finally, the control unit controls the hatch and the jet valve to close in turn, so that the aircraft body can continue underwater search. During the entire drone release process, the entrance and exit formed after the hatch is opened is always above the water surface, which can prevent the drone from contacting the seawater, ensuring that the drone is successfully released and will not be damaged by the seawater.

[0022] Correspondingly, during the process of recovering the drone, the jet valve is also in the open state, thereby ensuring that the entrance and exit formed after the hatch is opened is always above the water surface, preventing the drone from coming into contact with seawater.

[0023] To achieve the above purpose, the technical solution of the underwater unmanned vehicle provided by the present invention is: An underwater unmanned vehicle comprises a vehicle body and a drone carried on the vehicle body, the vehicle body comprising a storage bin for carrying the drone, the storage bin having an openable hatch, the vehicle body being provided with a jet port, a control unit, a high-pressure gas source storing high-pressure gas, and a jet channel connecting the high-pressure gas source and the jet port, a jet valve being provided at the jet channel and / or the jet port, the control unit being used to control the opening and closing of the jet valve, the jet valve having a closed state and an open state for allowing high-pressure gas to be ejected from the jet port so that the hatch is above the water surface, the control unit being used to control the hatch to open when the jet valve is in the open state, and sequentially controlling the hatch and the jet valve to close after the drone is released or recovered.

[0024] Furthermore, jet wings are provided on both sides of the aircraft body, and the jet ports are located at the tail ends of the jet wings.

[0025] Furthermore, a storage cabin is provided on the aircraft body, and the jet wing has a stowed state in which it is located inside the storage cabin to reduce the resistance encountered by the aircraft body when sailing underwater, and an expanded state outside the storage cabin. The control unit is used to control the opening of the jet valve when the jet wing is in the expanded state.

[0026] Furthermore, the jet port and the hatch are both located at the head of the vehicle body.

[0027] Furthermore, the direction of the jet port is perpendicular to the axial direction of the aircraft body.

[0028] Furthermore, the high-pressure gas source is a high-pressure gas tank detachably installed in a storage bin.

[0029] Furthermore, a launching device for launching the UAV is provided in the storage compartment.

[0030] Furthermore, the ejection device includes an ejection seat for launching the UAV, a compression elastic member is provided between the bottom wall of the storage bin and the ejection seat, a telescopic mechanism is also provided in the storage bin, a slot for inserting the telescopic mechanism is provided on the ejection seat, the telescopic mechanism has a longer state in which the compression elastic member is inserted into the slot when the compression elastic member is compressed, and a shorter state in which the telescopic mechanism is not inserted into the slot; the control unit is used to control the telescopic mechanism to switch from a longer state to a shorter state, so that the compression elastic member is reset and the UAV is ejected.

[0031] Furthermore, the hatch cover is located on the outer peripheral surface of the aircraft body, and the hatch cover and the jet port are respectively located on opposite sides of the aircraft body.

[0032] The beneficial effects of the underwater unmanned vehicle of the present invention are as follows: the present invention is an improved invention. In the present invention, the vehicle body is provided with an air jet, an air jet valve and a high-pressure gas source. When in use, the unmanned aerial vehicle can be carried in the storage bin, and the unmanned aerial vehicle can be transported to the area to be searched by the vehicle body.

[0033] During the release of the drone, the control unit controls the jet valve to be in the open state, and high-pressure gas is ejected from the jet port, thereby providing an upward force to the aircraft body to keep the hatch above the water surface; then, the control unit controls the hatch to open, so that the drone can be released from the storage compartment; finally, the control unit controls the hatch and the jet valve to close in turn, so that the aircraft body can continue underwater search. During the entire drone release process, the entrance and exit formed after the hatch is opened is always above the water surface, which can prevent the drone from contacting the seawater, ensuring that the drone is successfully released and will not be damaged by the seawater.

[0034] Correspondingly, during the process of recovering the drone, the jet valve is also in the open state, thereby ensuring that the entrance and exit formed after the hatch is opened is always above the water surface, preventing the drone from coming into contact with seawater. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 is a schematic structural diagram of a first underwater unmanned vehicle of the present invention (without showing the hatch); Figure 2 A schematic diagram of the structure of the second underwater unmanned vehicle of the present invention when navigating underwater (without showing the hatch); Figure 3 It is a structural schematic diagram of the second underwater unmanned vehicle of the present invention at the first moment when the drone is released (the hatch is not shown); Figure 4 A schematic diagram of the structure of the second underwater unmanned vehicle of the present invention at the second moment when the drone is released (the hatch is not shown); Figure 5 It is a structural schematic diagram of the second underwater unmanned vehicle of the present invention when releasing a drone at the third moment (the hatch is not shown); Figure 6 for Figure 5 Schematic diagram of the structure of the ejection device.

[0036] Description of reference numerals: 1. Aircraft body; 2. Jet wing; 3. Jet nozzle; 4. High-pressure gas tank; 5. Jet valve; 6. Storage compartment; 7. UAV; 8. Ejection device; 81. Motor; 82. Telescopic rod; 83. Compression spring; 84. Ejection seat; 9. Water surface. DETAILED DESCRIPTION

[0037] In order to solve the problems in the background technology, the core inventive concept of the present invention is: using high-pressure airflow to make the hatch cover higher than the water surface, and then controlling the hatch cover to open to release or recover the drone, thereby preventing the drone from contacting the sea water.

[0038] The present invention is further described in detail below in conjunction with embodiments.

[0039] The specific embodiment of the underwater unmanned vehicle provided by the present invention is as follows: like Figures 1 to 6As shown, as the first basic specific implementation method, the underwater unmanned vehicle includes a vehicle body 1 and a drone 7 carried on the vehicle body 1, the vehicle body 1 includes a storage compartment 6 for carrying the drone 7, the drone 7 is carried in the storage compartment 6, the storage compartment 6 has an openable hatch, the vehicle body 1 is provided with a jet port 3, a control unit, a high-pressure gas source storing high-pressure gas and a jet channel connecting the high-pressure gas source and the jet port 3, a jet valve 5 is provided at the jet channel and / or the jet port 3, the control unit is used to control the opening and closing of the jet valve 5, the jet valve 5 has a closed state and an open state for allowing high-pressure gas to be ejected from the jet port 3 to make the hatch above the water surface 9, the control unit is used to control the hatch to open when the jet valve 5 is in the open state, and to control the hatch and the jet valve 5 to close in sequence after the drone 7 is released or recovered.

[0040] In order to reduce the resistance encountered by the aircraft body 1 when sailing underwater, the shape of the aircraft body 1 is a rotary fluid dynamic shape. Of course, the aircraft body 1 can also be a teardrop shape or other shapes that encounter less resistance when sailing underwater.

[0041] In the 1-1 type of specific implementation, a high-pressure air chamber is provided on the aircraft body 1, and the jet valve 5 is installed at the inlet of the jet channel (or the outlet of the high-pressure air chamber).

[0042] In the 1-2 specific implementation manner, what is different from the 1-1 specific implementation manner is that the jet valve 5 is installed at the jet port 3 .

[0043] In the 1-3 type of specific implementation, what is different from the 1-1 type of specific implementation is that the jet valve 5 is installed in the middle of the jet channel.

[0044] In the 1-4 specific implementation manner, what is different from the 1-1 specific implementation manner is that the jet valve 5 is installed at the jet port 3 and the jet channel at the same time.

[0045] In the present invention, the installation position of the jet valve 5 is not limited, as long as the jet valve 5 can prevent the high-pressure gas from being ejected from the jet port 3 when closed and enable the high-pressure gas to be ejected from the jet port 3 when opened.

[0046] In the specific implementation of category 1-5, what is different from the specific implementation of category 1-1 is: Figures 1 to 6 As shown, the high-pressure gas source is a high-pressure gas tank 4 detachably installed in the storage bin 6, and the high-pressure gas can be quickly replenished for the aircraft body 1 by replacing the high-pressure gas tank 4. At the same time, the high-pressure gas tank 4 is located in the storage bin 6, and compared with the technical solution of additionally setting a chamber for accommodating the high-pressure gas tank 4, there is no need to additionally set a chamber for accommodating the high-pressure gas tank 4, and the structure is simple.

[0047] In the present invention, the aircraft body 1 is provided with an air jet 3, an air jet valve 5 and a high-pressure air source. When in use, the drone 7 can be carried in the storage bin 6, and the drone 7 can be transported to the search area by the aircraft body 1, thereby saving the energy of the drone 7 and extending the working time of the drone 7. When performing the search work, the staff only needs to remotely monitor the data sent back by the aircraft body 1 and the drone 7 on the ship or in the shore base, which can effectively save manpower and material resources.

[0048] During the process of releasing the drone 7, the control unit controls the jet valve 5 to be in an open state, and high-pressure gas is ejected from the jet port 3, thereby providing an upward force to the aircraft body 1, so that the hatch is higher than the water surface 9; then, the control unit controls the hatch to open, so that the drone 7 can be released from the storage bin 6; finally, the control unit controls the hatch and the jet valve 5 to close in turn, so that the aircraft body 1 can continue the underwater search. During the entire process of releasing the drone 7, the entrance and exit formed after the hatch is opened is always higher than the water surface 9, which can prevent the drone 7 from contacting the seawater, and ensure that the drone 7 is successfully released and will not be damaged by the seawater.

[0049] Accordingly, during the process of recovering the drone 7, the jet valve 5 is also in an open state, thereby ensuring that the entrance and exit formed after the hatch is opened is always above the water surface 9, thereby preventing the drone 7 from contacting the seawater.

[0050] In the first type of specific implementation, the air jet 3 is directly disposed on the aircraft body 1 .

[0051] Compared with the first embodiment, in order to increase the lift force on the aircraft body 1, in the second embodiment, Figures 1 to 6 As shown, jet wings 2 are provided on both sides of the aircraft body 1, and the jet port 3 is located at the tail end of the jet wing 2. At this time, after the high-pressure gas hits the water surface 9, part of the gas will return to exert an upward force on the jet wing 2, thereby increasing the lift exerted on the aircraft body 1 and enabling the aircraft body 1 to better emerge from the water.

[0052] In the 2-1 type of specific implementation, the jet wing 2 is fixed on the aircraft body 1. When the aircraft body 1 is sailing underwater, the jet wing 2 is subject to greater resistance, resulting in greater resistance to the aircraft body 1, which leads to lower maximum cruising speed and maximum cruising range of the aircraft body 1. Although it does not affect normal use, the aircraft body 1 needs to be frequently recharged.

[0053] In order to improve the maximum navigation speed and maximum cruising range of the aircraft body 1, in the specific implementation of type 2-2, the difference from the specific implementation of type 2-1 is that: the aircraft body 1 is provided with a storage compartment, and the jet wing 2 has a storage state located in the storage compartment to reduce the resistance of the aircraft body 1 when sailing underwater and an expanded state located outside the storage compartment, and the control unit is used to control the jet valve 5 to open when the jet wing 2 is in the expanded state. When the aircraft body 1 is sailing underwater, the jet wing 2 can be switched to the storage state, thereby reducing the resistance of the aircraft body 1 and improving the maximum navigation speed and maximum cruising range of the aircraft body 1.

[0054] In the specific implementation of Class 2-2-1, if Figures 1 to 5 As shown, the jet wing 2 is rotatably mounted on the aircraft body 1. Figure 2 As shown, when the aircraft body 1 is navigating underwater, the jet wings 2 are folded into the receiving groove, thereby reducing the resistance of the aircraft body 1. When releasing the drone 7, first, as shown in FIG. Figure 3~4 As shown, the jet wing 2 is switched from the stowed state to the unfolded state; thereafter, as shown Figure 5 As shown, the jet nozzle 3 ejects air, the hatch opens after leaving the water surface 9, and the drone 7 leaves the storage bin 6 from the entrance; finally, refer to Figures 2~4 As shown, the jet port 3 stops jetting, and the jet wing 2 switches from the deployed state to the retracted state.

[0055] Accordingly, when recovering the drone 7, first, refer to Figure 3~4 As shown, the jet wing 2 is switched from the stowed state to the unfolded state; thereafter, referring to Figure 5 As shown, the jet nozzle 3 sprays air, the hatch opens after leaving the water surface 9, and the drone 7 enters the storage bin 6 from the entrance; finally, refer to Figures 2~4 As shown, the jet port 3 stops jetting, and the jet wing 2 switches from the deployed state to the retracted state.

[0056] In the 2-2-2 type of specific embodiment, the jet wing 2 is retractably mounted on the aircraft body 1 .

[0057] It should be noted that, when the maximum cruising speed of the aircraft body 1 is higher, the time it takes for the aircraft body 1 to reach the designated search area is shorter, the search starts earlier after a shipwreck occurs, and the survival rate of the victims is higher.

[0058] In order to optimize the water discharge effect of the aircraft body 1, the position of the jet port 3 is improved as follows in the present invention: In the preferred third embodiment, the jet port 3 and the hatch cover are both located at the head of the aircraft body 1. At this time, the height at which the aircraft body 1 needs to be out of the water is relatively small, which is conducive to allowing the hatch cover to completely leak out of the water surface 9.

[0059] In the fourth type of specific implementation, what is different from the third type of specific implementation is that the hatch cover is located in the middle of the aircraft body 1. In this case, the height at which the aircraft body 1 is out of the water is higher.

[0060] In the 4-1 type of specific implementation, compared with the 3rd type of specific implementation, the gas pressure in the high-pressure gas source is higher, so that the aircraft body 1 can be out of the water at a higher height, ensuring that the hatch cover is completely out of the water.

[0061] In the 4-2 type of specific implementation manner, the jet outlets 3 are simultaneously arranged at the head and the middle part of the aircraft body 1. When the aircraft body 1 is out of water, the jet outlets 3 at the head spray out first, and then the jet outlets 3 at the middle spray out, so that the aircraft body 1 can be out of water to a higher height, ensuring that the hatch cover is completely out of water.

[0062] In order to further optimize the water discharge effect of the aircraft body 1, the direction of the jet port 3 is improved as follows in the present invention: In the preferred fifth embodiment, the direction of the jet port 3 is perpendicular to the axial direction of the aircraft body 1. At this time, when the hatch cover is completely out of water, the aircraft body 1 is in a tilted state. By controlling the pressure of the high-pressure gas, the inclination angle of the aircraft body 1 can be conveniently controlled to adjust the release angle of the drone 7.

[0063] In the preferred sixth embodiment, the direction of the jet nozzle 3 is parallel to the axial direction of the aircraft body 1. At this time, the same as in the invention patent with the authorization announcement number CN113212713B is that when the hatch cover is completely out of water, the aircraft body 1 is in a vertical state. In the sixth embodiment, the release angle and recovery angle of the drone 7 cannot be adjusted, but it does not affect the release and recovery of the drone 7.

[0064] In other specific embodiments, the direction of the jet port 3 is neither parallel nor perpendicular to the axial direction of the aircraft body 1. The component of the force exerted by the high-pressure gas on the aircraft body 1 is used to provide lift for the aircraft body 1. The lift exerted on the aircraft body 1 is small, and it is necessary to adaptively increase the pressure of the high-pressure gas or adjust the number and position of the jet port 3.

[0065] In order to increase the release speed of the drone 7, the present invention makes the following improvements to the release method of the drone 7: In the seventh specific implementation manner, an ejection device 8 for ejecting the drone 7 is provided in the storage bin 6. The drone 7 can be quickly ejected through the ejection device 8. On the one hand, the release time of the drone 7 can be shortened, so that the drone 7 can quickly start to perform search work and improve the survival rate of the victims; on the other hand, the drone 7 can be quickly separated from the sea surface, thereby completing the release of the drone 7 on the rough sea surface.

[0066] In the 7-1 specific embodiment, the ejection device 8 includes an ejection seat 84 for launching the drone 7, a compression elastic member is provided between the bottom wall of the storage bin 6 and the ejection seat 84, a telescopic mechanism is also provided in the storage bin 6, and a slot for inserting the telescopic mechanism is provided on the ejection seat 84, and the telescopic mechanism has a longer state in which the compression elastic member is inserted into the slot when the compression elastic member is compressed and a shorter state in which the telescopic mechanism is not inserted into the slot; the control unit is used to control the telescopic mechanism to switch from the longer state to the shorter state, so that the compression elastic member is reset and the drone 7 is ejected, and the structure is simple. Among them, the compression elastic member is preferably a compression spring 83, and the telescopic mechanism is preferably an electric telescopic rod composed of a motor 81 and a telescopic rod 82.

[0067] When recovering the drone, first, the drone contacts the ejection seat 84 and squeezes the compressed elastic member, then the telescopic mechanism switches from a shorter state to a longer state; finally, the drone switches to a standby state to save energy of the drone.

[0068] In the specific implementation of category 7-2, the ejection device 8 is a conventional electromagnetic ejection device 8. For example, a magnet is provided on the drone 7, and the ejection device 8 is an electromagnet. When the ejection is not performed, the electromagnet is not energized, and at this time, the magnet of the drone 7 is adsorbed on the electromagnet; when the ejection is performed, the electromagnet is energized, and the magnetic pole of the electromagnet is opposite to the magnetic pole of the magnet of the drone 7, thereby ejecting the drone 7.

[0069] In the eighth embodiment, the aircraft body 1 does not include the ejection device 8 , and the drone 7 moves out of the storage bin 6 on its own.

[0070] It should be noted that the underwater unmanned aerial vehicle corresponding to the eighth specific implementation method cannot be used in a harsh environment with rough sea waves, but can only be used in a normal environment with small sea waves. When using the underwater unmanned aerial vehicle corresponding to the seventh specific implementation method, if the sea surface conditions are too severe and the drone 7 cannot land safely in the storage bin 6, the drone 7 can be landed on the ship, and the staff can recover the drone 7 and the underwater unmanned aerial vehicle separately.

[0071] In order to reduce the impact of high-pressure gas on the drone 7, the present invention imposes the following restrictions on the location of the hatch: In the ninth embodiment, the hatch is located on the outer peripheral surface of the aircraft body 1, and the hatch and the jet port 3 are respectively located on opposite sides of the aircraft body 1, thereby reducing the impact of high-pressure gas on the drone 7.

[0072] In the 10th category of specific implementations, the same as in the invention patent with authorization announcement number CN113212713B is that the hatch is located at the front end of the aircraft body 1, and the drone 7 leaves the storage bin 6 along the axial direction of the aircraft body 1.

[0073] The specific embodiment of the aircraft body 1 provided by the present invention is as follows: Reference Figures 1 to 6 As shown, the difference between the aircraft body 1 provided by the present invention and the underwater unmanned aircraft is that the aircraft body 1 does not include the drone 7, and the underwater unmanned aircraft includes both the aircraft body 1 and the drone 7. The specific structure of the aircraft body 1 in this embodiment is the same as the specific structure of the aircraft body 1 in any specific implementation of the underwater unmanned aircraft of the present invention, and will not be repeated here.

[0074] It should be noted that the present invention only classifies the specific embodiments according to specific features, which does not mean that other categories do not contain this specific feature. For example, the structure of the first category of specific embodiments may be the same as that of the third or fifth category of specific embodiments.

[0075] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions recorded in the aforementioned embodiments without creative work, or to replace some of the technical features therein with equivalents, or to organically combine different types of specific implementations, thereby combining the attached Figures 1 to 6 The two specific implementations are given in the figure. Of course, those skilled in the art can also combine the specific implementations not given in the other drawings of the specification. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aircraft body, comprising a storage compartment for carrying an unmanned aerial vehicle, the storage compartment having an openable hatch, characterized in that: The aircraft body is provided with a jet port, a control unit, a high-pressure gas source storing high-pressure gas and a jet channel connecting the high-pressure gas source and the jet port. A jet valve is provided at the jet channel and / or the jet port. The control unit is used to control the opening and closing of the jet valve. The jet valve has a closed state and an open state for allowing high-pressure gas to be ejected from the jet port so that the hatch cover is above the water surface. The control unit is used to control the hatch cover to open when the jet valve is in the open state, and to control the hatch cover and the jet valve to close in sequence after the UAV is released or recovered.

2. The aircraft body according to claim 1, characterized in that: Jet wings are arranged on both sides of the aircraft body, and the jet ports are located at the tail ends of the jet wings.

3. The aircraft body according to claim 2, characterized in that: A storage cabin is provided on the aircraft body. The jet wing has a stowed state in which it is located inside the storage cabin to reduce the resistance encountered by the aircraft body when sailing underwater, and an expanded state outside the storage cabin. The control unit is used to control the opening of the jet valve when the jet wing is in the expanded state.

4. The aircraft body according to any one of claims 1 to 3, characterized in that: The jets and hatches are located at the head of the vehicle body.

5. The aircraft body according to any one of claims 1 to 3, characterized in that: The direction of the jet nozzle is perpendicular to the axial direction of the aircraft body.

6. The aircraft body according to any one of claims 1 to 3, characterized in that: The high-pressure gas source is a high-pressure gas tank detachably installed in the storage bin.

7. The aircraft body according to any one of claims 1 to 3, characterized in that: There is a catapult device in the storage compartment for launching drones.

8. The aircraft body according to claim 7, characterized in that: The ejection device includes an ejection seat for launching the UAV, a compression elastic member is provided between the bottom wall of the storage bin and the ejection seat, a telescopic mechanism is also provided in the storage bin, a slot for inserting the telescopic mechanism is provided on the ejection seat, the telescopic mechanism has a longer state in which the compression elastic member is inserted into the slot when the compression elastic member is compressed, and a shorter state in which the telescopic mechanism is not inserted into the slot; the control unit is used to control the telescopic mechanism to switch from the longer state to the shorter state, so that the compression elastic member is reset and the UAV is ejected.

9. The aircraft body according to any one of claims 1 to 3, characterized in that: The hatch cover is located on the outer peripheral surface of the aircraft body, and the hatch cover and the jet port are respectively located on opposite sides of the aircraft body.

10. An underwater unmanned vehicle, comprising a vehicle body and a drone mounted on the vehicle body, characterized in that: The aircraft body is the aircraft body described in any one of claims 1 to 9.

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