A disposable independent monitoring camera for flight training aircraft in emergency situation

Abstract

The present application discloses an independent surveillance camera that can be thrown away in an emergency state for a flight training aircraft, which relates to the technical field of image communication equipment, and comprises a rotating column assembly, a camera assembly, a pulling rope assembly and an ejection assembly; a passage is arranged near the top of a cabin shell; the rotating column assembly comprises a rotating column and a supporting displacement assembly; the supporting displacement assembly is used to drive the rotating column to move relative to or toward each other; the camera assembly comprises a containing shell and a camera body; the camera body is fixed to the bottom of the containing shell; the pulling rope assembly comprises a central rope, a hollow rod, a supporting frame, a retracting assembly and a positioning frame assembly, wherein the number of the hollow rods is multiple and is sleeved on the central rope; the retracting assembly is a winch structure fixed on the supporting frame; one end of the central rope is fixed on the positioning frame assembly positioned on the containing shell, and the other end is positioned on the retracting assembly; the technical effect that the surveillance camera can record the state of the aircraft from an external perspective during flight training is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of image communication equipment, and in particular to a disposable independent monitoring camera for a flight training aircraft in an emergency state. Background Art

[0002] Practical flight training is a compulsory course for pilots. During training, students are required to fly training aircraft for flight training.

[0003] Due to lack of actual driving experience, trainees sometimes deal improperly with unexpected problems (faults, aircraft attitude problems), which leads to aggravated faults or unstable flight attitude. In order to discover and correct errors, after getting off the training aircraft, it is necessary to combine the flight data stored in the aircraft and the pilot's memories to restore and analyze the errors in the flight process so as to make progress and avoid the recurrence of errors. In order to solve the above problems, in the prior art, surveillance cameras are usually installed in the cockpit to record the trainees' operation process, and the recorded data is used as an important basis for error correction.

[0004] However, when reconstructing a flight process with errors, information such as the training aircraft's specific flight attitude and appearance status (real-time damage points) is equally important. However, due to the lack of an external perspective, the above information cannot be obtained, resulting in unclear flight status of the aircraft, which in turn brings certain difficulties to discovering, judging and correcting errors. Summary of the invention

[0005] The embodiment of the present application solves the technical problem in the prior art that the monitoring camera of a flight training aircraft cannot record the appearance status of the aircraft during flight training by providing an independent disposable monitoring camera for emergency situations of a flight training aircraft, thereby achieving the technical effect that the monitoring camera can record the aircraft status from an external perspective during flight training.

[0006] The embodiment of the present application provides a flight training aircraft emergency state throwable independent monitoring camera, including a rotating column assembly, a camera assembly, a pulling rope assembly and a ejection assembly;

[0007] A passage is provided near the top of the cabin shell, on which a sealing diaphragm is fixed;

[0008] The rotating column assembly comprises a rotating column and a supporting displacement assembly, and the rotating column rotates under the drive of the column rotation driving assembly;

[0009] The support displacement assembly is a telescopic rod structure fixed to the cabin shell, used to drive the rotating column to move relative or toward each other and thus clamp the pulling rope assembly in time;

[0010] The camera assembly comprises a housing and a camera body; the housing is a container; the camera body is a ball head camera, fixed at the bottom of the housing;

[0011] The pulling rope assembly includes a central rope, a hollow rod, a support frame, a retracting assembly and a positioning frame assembly, and there are multiple hollow rods, which are sleeved on the central rope;

[0012] The retractable assembly is a winch structure fixed on the support frame;

[0013] One end of the central rope is fixed to a positioning frame assembly positioned on the accommodating shell, and the other end is positioned on the retractable assembly;

[0014] The ejection assembly is used to eject the camera assembly out of the training machine.

[0015] Preferably, it also includes a protective capsule;

[0016] The protective sac is fixed on the containing shell to play a buffering role and prevent the containing shell from being damaged by collision; the protective sac is tubular and / or annular.

[0017] Preferably, it also includes a detachable assembly, a parachute assembly and an in-shell control assembly;

[0018] The detaching component is positioned on the accommodating shell and the positioning frame component, and is used to timely detach the accommodating shell from the positioning frame component, and is a buckle, an electric heating body or an electric pin;

[0019] The parachute assembly is fixed on the containing shell and is controlled by the control assembly in the shell;

[0020] The in-shell control component is connected to the training machine control unit signal, fixed inside the accommodating shell, and is used to control the detaching component and the parachute component to operate in a timely manner.

[0021] Furthermore, the control component inside the shell is electrically connected to the control unit of the training machine through a signal transmission line. The signal transmission lines are fixed on the center rope. There are two signal transmission lines. The two signal transmission lines are plugged together at the connection position between the accommodating shell and the positioning frame assembly; the two signal transmission lines are disconnected when the accommodating shell and the positioning frame assembly are separated.

[0022] Preferably, the protective capsule comprises a tubular capsule, a connecting soft plate and an annular capsule;

[0023] The interior of the accommodating shell also includes an air chamber and a valve body;

[0024] The tubular capsule is sleeved on the containing shell, and the inner circle diameter is larger than the circumscribed circle diameter of the containing shell;

[0025] The connecting soft plate is a rubber soft plate, the main body is annular, the inner ring is fixed on the outer wall of the containing shell, and the outer ring is fixed on the top of the tubular capsule;

[0026] The cross section of the assembly connecting the soft plate and the tubular capsule is an inverted V shape before the annular capsule expands; the annular capsule is fixed on the outer wall of the housing and communicated with the air chamber body, and the valve body is positioned on the communication channel to control the opening and closing of the channel;

[0027] The air chamber is filled with compressed gas; the operation of the valve body is controlled by a control component in the shell;

[0028] The valve body starts to operate after the parachute assembly operates, opens the channel and causes the annular capsule to expand, and the expansion of the annular capsule squeezes the connecting soft plate and causes the tubular capsule to move downward to cover the camera body.

[0029] Preferably, the rotating column comprises a column body and a soft layer;

[0030] The column is a cylinder, and the soft layer is a rubber tube with a thickness greater than 5 mm. The soft layer is coated on the side wall of the column and is coaxial with the column.

[0031] Preferably, a hemispherical rod head projection is positioned at one end of the hollow rod, and a rod head recess that cooperates with the rod head projection is positioned at the other end.

[0032] Furthermore, the ejection assembly includes a limit frame, a sliding plate, a support rod, an energy storage compression spring and a force storage assembly;

[0033] The limit frame is a frame structure, fixed on the cabin shell, located directly below the camera assembly, and is used to limit the movement of the sliding plate so that the sliding plate can only move vertically upward or downward;

[0034] The sliding plate is slidably positioned on the limiting frame;

[0035] The support rods are arranged vertically, in multiple numbers, and one end away from the sliding plate abuts against the camera assembly; the energy storage compression spring is positioned below the sliding plate and is used to store and release elastic potential energy;

[0036] The energy storage component is a winch structure, which is used to pull the sliding plate downward and thus cause the energy storage compression spring to accumulate elastic potential energy, and includes a winch and a winch rope;

[0037] The winch is fixed at the bottom of the limit frame, one end of the winch rope is fixed on the winch, and the other end is fixed on the sliding plate; when ejection is required, the winch releases the winch rope, and the energy storage compression spring releases the elastic potential energy.

[0038] Preferably, the central rope includes an elastic portion and a non-elastic portion, the elastic portion is made of elastic rubber, and the elastic portion and the non-elastic portion are both rope bodies, which are alternately arranged and fixed together.

[0039] Preferably, the detachable component is a heating plate, which is an electric heating plate, electrically connected to the power supply component in the shell and controlled by the control component in the shell, fixed at the connection position between the accommodating shell and the positioning frame component, and the positioning frame component is fixed to the accommodating shell or the heating plate by glue; the heating plate heats up to cause the glue to fail.

[0040] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:

[0041] By adding a monitoring camera including a rotating column assembly, a camera assembly, a pulling rope assembly and an ejection assembly to a flight training aircraft, the camera assembly can be manipulated to eject the training aircraft when an emergency occurs in the training aircraft, and the aircraft status information can be recorded from an external perspective. The pulling rope assembly is used in conjunction with the rotating column assembly to support the camera assembly after it flies out of the training aircraft and to retract it in a timely manner. This effectively solves the technical problem in the prior art that the monitoring camera of a flight training aircraft cannot record the appearance status of the aircraft during flight training, thereby achieving the technical effect that the monitoring camera can record the aircraft status from an external perspective during flight training. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 It is a schematic diagram of the appearance structure of the disposable independent monitoring camera in emergency state of the flight training aircraft of the present invention;

[0043] Figure 2 It is a schematic diagram of the positional relationship between the rotating column assembly and the camera assembly of the emergency disposable independent monitoring camera of the flight training aircraft of the present invention;

[0044] Figure 3 It is a schematic diagram of the positional relationship of the rotating column assembly of the emergency disposable independent monitoring camera of the flight training aircraft of the present invention;

[0045] Figure 4 A simplified diagram of the internal structure of a camera assembly of an emergency-disposable independent monitoring camera for a flight training aircraft according to the present invention;

[0046] Figure 5 A schematic diagram of the positional relationship between a camera assembly and an ejection assembly of an emergency-disposable independent monitoring camera for a flight training aircraft according to the present invention;

[0047] Figure 6 A schematic diagram of the positional relationship between a pull rope assembly and a camera assembly of a disposable independent monitoring camera for an emergency state of a flight training aircraft according to the present invention;

[0048] Figure 7 It is a structural schematic diagram of the ejection assembly of the independent disposable monitoring camera of the flight training aircraft in emergency state of the present invention;

[0049] Figure 8It is a schematic diagram of the positional relationship between the rotating column and the hollow rod of the emergency throwable independent monitoring camera of the flight training aircraft of the present invention;

[0050] Fig. 9 It is a structural schematic diagram of a hollow rod of a disposable independent monitoring camera in an emergency state of a flight training aircraft according to the present invention;

[0051] Fig.10 A simplified structural diagram of a camera assembly of a disposable independent monitoring camera for an emergency state of a flight training aircraft according to the present invention;

[0052] Fig.11 A schematic diagram of the positional relationship between the parachute assembly and the accommodating shell of the emergency throwable independent monitoring camera of the flight training aircraft of the present invention;

[0053] Fig.12 It is a schematic diagram of the positional relationship between the annular capsule and the camera body of the emergency disposable independent monitoring camera of the flight training aircraft of the present invention;

[0054] Fig.13 It is a schematic diagram of the positional relationship between the tubular bag and the connecting soft board of the emergency disposable independent monitoring camera of the flight training aircraft of the present invention;

[0055] Fig.14 The present invention is a simplified structural diagram of the center rope of the independent monitoring camera that can be thrown away in an emergency state of the flight training aircraft.

[0056] In the figure:

[0057] Nacelle shell 100, passage 110, sealing diaphragm 120;

[0058] Rotating column assembly 200, rotating column 210, column body 211, soft layer 212, support shift assembly 220, support rod 221, carrier body 222, column body rotation driving assembly 230;

[0059] Camera assembly 300, housing 310, camera body 320, power supply assembly 330 in the housing, storage assembly 340, protective capsule 350, tubular capsule 351, connecting soft board 352, annular capsule 353, parachute assembly 360, control assembly 370 in the housing, air chamber 380, valve body 390;

[0060] Pull rope assembly 400, center rope 410, elastic part 411, non-elastic part 412, hollow rod 420, rod head protrusion 421, rod head pit 422, support frame 430, retractable assembly 440, guide wheel body 450, positioning frame assembly 460, heating plate 470;

[0061] The ejection assembly 500 , the limiting frame 510 , the sliding plate 520 , the support rod 530 , the energy storage compression spring 540 , the force storage assembly 550 , the winch 551 , and the winch rope 552 . DETAILED DESCRIPTION

[0062] To facilitate the understanding of the present invention, the present application will be described more comprehensively below with reference to the relevant drawings; the drawings show preferred embodiments of the present invention, but the present invention can be implemented in many different forms and is not limited to the embodiments described herein; on the contrary, the purpose of providing these embodiments is to enable a more thorough and comprehensive understanding of the disclosed content of the present invention.

[0063] It should be noted that the terms “vertical”, “horizontal”, “up”, “down”, “left”, “right” and similar expressions used in this document are only for illustrative purposes and do not represent the only implementation method.

[0064] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which the present invention belongs; the terms used in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention; the term "and / or" used herein includes any and all combinations of one or more related listed items.

[0065] See also Figure 1 , which is a schematic diagram of the appearance structure of the independent disposable monitoring camera for emergency state of the flight training aircraft of the present invention; the present application adds an independent monitoring camera including a rotating column assembly 200, a camera assembly 300, a pulling rope assembly 400 and an ejection assembly 500 to the flight training aircraft, so as to operate the camera assembly 300 to eject the training aircraft when an emergency state occurs in the training aircraft, and record the aircraft status information from an external perspective; the pulling rope assembly 400 is used to cooperate with the rotating column assembly 200 to support the camera assembly 300 after the camera assembly 300 flies out of the training aircraft and retract it in time; the technical effect that the monitoring camera can record the aircraft status from an external perspective during the flight training process is achieved.

[0066] Embodiment 1

[0067] like Figure 1 As shown, the independent disposable monitoring camera for emergency situations of the flight training aircraft of the present application is installed on the cabin shell 100 , and includes a rotating column assembly 200 , a camera assembly 300 , a pulling rope assembly 400 and an ejection assembly 500 .

[0068] The cabin shell 100 is the outer shell of the flight training cabin. A passage 110 is provided near the top of the cabin shell 100 for facilitating the entry and exit of the camera assembly 300. The passage 110 is a through hole on which a sealing diaphragm 120 is fixed; the sealing diaphragm 120 is used to close the passage 110 and is preferably made of rubber.

[0069] like Figure 2 and Figure 3 As shown, the rotating column assembly 200 is fixed on the cabin shell 100, and is used to cooperate with the pulling rope assembly 400 to fix the camera assembly 300 and assist in the retraction of the camera assembly 300; the rotating column assembly 200 includes a rotating column 210, a support displacement assembly 220 and a column rotation drive assembly 230; the number of the rotating columns 210 and the support displacement assembly 220 are both two, the rotating column 210 is cylindrical, and rotates around its own axis under the drive of the column rotation drive assembly 230; the two rotating columns 210 are arranged opposite to each other, and are respectively rotatably connected to two different support displacement assemblies 220; the support displacement assembly 220 is a telescopic rod structure, fixed on the cabin shell 100, controlled by the control unit of the training machine, and used to drive the two rotating columns 210 to move relative to or towards each other under the passage 110; the column rotation drive assembly 230 is positioned on the rotating column 210 or the support displacement assembly 220, and is preferably a motor, with one or more number, used to drive one or two rotating columns 210 to rotate;

[0070] Furthermore, the rotating column 210 includes a column 211 and a soft layer 212; the column 211 is a cylinder, and the soft layer 212 is a rubber tube with a thickness greater than 5 mm, which is coated on the side wall of the column 211 and is coaxial with the column 211;

[0071] Further, such as Figure 3 As shown, the support displacement assembly 220 includes a support rod 221 and a carrier 222; there are two support rods 221, both of which are slidably positioned on the carrier 222 along the same direction; the carrier 222 is fixed on the cabin shell 100, and is a block or a plate; the two ends of the rotating column 210 are respectively rotatably connected to the two support rods 221.

[0072] like Figure 4As shown, the camera assembly 300 is used to record image information, including a housing shell 310, a camera body 320, an in-shell power supply assembly 330, a storage assembly 340 and a protective capsule 350; the housing shell 310 is a container for storing the in-shell power supply assembly 330 and the storage assembly 340; the camera body 320 is a ball head camera, fixed at the bottom of the housing shell 310, and used to collect image information; the in-shell power supply assembly 330 is a battery, used to provide energy for the operation of the camera body 320; the storage assembly 340 plays a role in storing image information; the protective capsule 350 is fixed on the housing shell 310, and plays a buffering role to prevent the housing shell 310 from collision and damage.

[0073] Preferably, the top of the accommodating shell 310 is sharp or fixed with spikes; the spikes of the accommodating shell 310 are used to pierce the sealing membrane 120.

[0074] Preferably, Figure 4 As shown, the protective capsule 350 is a tubular capsule 351 , and the tubular capsule 351 covers the camera assembly 300 .

[0075] Preferably, Fig.10 As shown, the protective capsule 350 is an annular annular capsule 353 , which is one or more in number and is fixed on the side wall of the accommodating shell 310 , and its axial direction is the same as the height direction of the accommodating shell 310 .

[0076] like Figure 5 and Figure 6As shown, the pulling rope assembly 400 is used to support the camera assembly 300, including a central rope 410, a hollow rod 420, a support frame 430, a retracting assembly 440, a guide wheel body 450 and a positioning frame assembly 460; the central rope 410 is a rope body; the hollow rod 420 is a rod body with a through hole therein, and the diameter of the through hole is not less than 1.2 times and not more than 2 times the diameter of the central rope 410; the length of the hollow rod 420 is greater than 4 cm and less than 15 cm, and there are multiple hollow rods 420, which are sleeved on the central rope 410 (strung into a string); the total length of the central rope 410 is greater than 5 meters and is 1.3 to 1.8 times the total length of all hollow rods 420 on the central rope 410; the support frame 430 is a frame structure, fixed On the cabin shell 100, it is used to support and position the retractable assembly 440 and the guide wheel body 450; the retractable assembly 440 is a winch structure, fixed on the support frame 430; the guide wheel body 450 is a cylindrical wheel, which is connected to the support frame 430 by rotation around its own axis, and the guide wheel body 450 has the same axial direction as the retractable assembly 440, and is used to guide the movement of the center rope 410; the positioning frame assembly 460 is fixed on the accommodating shell 310, preferably in a U-shape or a V-shape, and is used to provide a fixed point for the end of the center rope 410 directly below the camera body 320; one end of the center rope 410 is fixed on the positioning frame assembly 460, and the other end is positioned on the retractable assembly 440.

[0077] Preferably, Fig. 9 As shown, a hemispherical rod head protrusion 421 is positioned at one end of the hollow rod 420 , and a rod head recess 422 that cooperates with the rod head protrusion 421 is positioned at the other end.

[0078] The ejection assembly 500 is used to accumulate and release elastic potential energy and eject the camera assembly 300 out of the training machine in a timely manner; further, Figure 7As shown, the ejection assembly 500 includes a limit frame 510, a sliding plate 520, a support rod 530, an energy storage compression spring 540 and a force storage assembly 550; the limit frame 510 is a frame structure, fixed on the cabin shell 100, located directly below the camera assembly 300, and is used to limit the movement of the sliding plate 520, so that the sliding plate 520 can only move vertically upward or downward; the sliding plate 520 is slidably positioned on the limit frame 510; the support rod 530 is vertically arranged, and the number is multiple, and one end away from the sliding plate 520 abuts against the camera assembly 3 00; the energy storage compression spring 540 is positioned below the sliding plate 520, and is used to accumulate and release elastic potential energy; the force storage assembly 550 is a winch structure, which is used to pull the sliding plate 520 downward and thereby cause the energy storage compression spring 540 to accumulate elastic potential energy, and includes a winch 551 and a winch rope 552; the winch 551 is fixed to the bottom of the limit frame 510, one end of the winch rope 552 is fixed to the winch 551, and the other end is fixed to the sliding plate 520; when ejection is required, the winch 551 releases the winch rope 552, and the energy storage compression spring 540 releases the elastic potential energy.

[0079] A control button for controlling the operation of the ejection assembly 500 is positioned inside the training machine.

[0080] Preferably, a heating body is positioned at the top of the accommodating shell 310, and the heating body is controlled by the training machine control unit to assist in puncturing the sealing diaphragm 120; the training machine control unit is signal-connected to the power supply component 330 in the shell, and the power supply component 330 in the shell is electrically connected to the heating body.

[0081] When the independent disposable surveillance camera for emergency situations of the flight training aircraft of the embodiment of the present application is actually used:

[0082] 1. When facing an unexpected problem during driving of the training machine, the driver presses the control button to control the camera assembly 300 to be ejected; at this time, the ejection assembly 500 operates and the camera assembly 300 is ejected by impact;

[0083] 2. At the same time, the retracting assembly 440 releases the central rope 410, and after a specific time (preferably 3 to 5 seconds) the rotating column assembly 200 operates; Figure 8 As shown, the rotating columns 210 are moved closer to each other to fix one of the hollow rods 420 by clamping; thereafter, the retracting assembly 440 releases the central rope 410, causing the hollow rods 420 to automatically splice into straight rods under the action of tension;

[0084] 3. The camera body 320 captures an image;

[0085] 4. The driver presses the control button to control the center rope 410 to retract and the rotating column 210 to rotate, so as to gradually retract the camera assembly 300.

[0086] In order to prevent the central rope 410 from being broken due to the excessive speed of the retractable assembly 440 and the wind force, the central rope 410 is Fig.14 As shown, the center rope 410 includes an elastic portion 411 and a non-elastic portion 412 , the elastic portion 411 is made of elastic rubber, and the elastic portion 411 and the non-elastic portion 412 are both rope bodies, which are alternately arranged and fixed together.

[0087] Preferably, in order to prevent the hollow rod 420 from swinging significantly when supporting the camera assembly 300 , the number of the rotating columns 210 on the rotating column assembly 200 is 3 or more (to clamp and fix the hollow rod 420 ).

[0088] Preferably, the flight training aircraft of the present application has a disposable independent surveillance camera for emergency situations for use in conjunction with an in-cabin camera.

[0089] The technical solutions in the above embodiments of the present application have at least the following technical effects or advantages:

[0090] The present invention solves the technical problem in the prior art that the monitoring camera of a flight training aircraft cannot record the appearance status of the aircraft during flight training, and achieves the technical effect that the monitoring camera can record the aircraft status from an external perspective during flight training.

[0091] Embodiment 2

[0092] In order to further improve the practicality of the present application and ensure that the information collected by the independent monitoring camera is retained even if the training aircraft crashes, the present embodiment of the application adds a detachable component, a parachute component 360 and an in-shell control component 370 on the basis of the above embodiment; specifically:

[0093] like Fig.10 As shown, the detachable component is positioned on the accommodating shell 310 and the positioning frame component 460, and is used to disassemble the accommodating shell 310 from the positioning frame component 460 in a timely manner, and is a buckle, an electric heating body, an electric pin, etc.; further, the detachable component is a heating plate 470, and the heating plate 470 is an electric heating plate, which is electrically connected to the power supply component 330 in the shell and controlled by the control component 370 in the shell, and is fixed at the connection position between the accommodating shell 310 and the positioning frame component 460, and the positioning frame component 460 is fixed to the accommodating shell 310 or the heating plate 470 by glue; after the heating plate 470 is heated up, the glue fails;

[0094] like Fig.11 As shown, the parachute assembly 360 is fixed on the housing 310 and is controlled by the control assembly 370 in the housing to operate. This is a prior art and will not be described in detail here.

[0095] The in-shell control component 370 is a logic controller, which is connected to the training machine control unit by signal, fixed inside the accommodating shell 310, and is used to control the detaching component and the parachute component 360 to operate in a timely manner.

[0096] Preferably, the control component 370 in the shell is electrically connected to the control unit of the training machine through a signal transmission line. The signal transmission lines are fixed on the center rope 410. There are two signal transmission lines. The two signal transmission lines are plugged together at the connection position between the accommodating shell 310 and the positioning frame assembly 460 to form a signal path; the two signal transmission lines are disconnected when the accommodating shell 310 and the positioning frame assembly 460 are separated.

[0097] When the independent disposable monitoring camera for emergency situations of a flight training aircraft according to an embodiment of the present application is actually used: if the camera assembly 300 is ejected from the flight training aircraft for a specific time (preferably more than 30 seconds) and is still not dragged back (the training aircraft control unit has not received a towing operation instruction), the control assembly 370 in the shell controls the detachment assembly and the parachute assembly 360 to operate successively.

[0098] Preferably, when the training machine control unit receives a trainee parachuting signal, the detaching assembly and the parachute assembly 360 are operated successively.

[0099] In order to ensure that the camera assembly 300 is not easily damaged by collision and the camera body 320 is not blocked by the protective capsule 350 to affect the shooting, it is preferred that Fig.12 and Fig.13 As shown, the protective sac 350 includes a tubular sac 351, a connecting soft plate 352 and an annular sac 353; the interior of the accommodating shell 310 also includes an air chamber 380 and a valve body 390; the tubular sac 351 is sleeved on the accommodating shell 310, and the inner circle diameter is larger than the circumscribed circle diameter of the accommodating shell 310; the connecting soft plate 352 is a rubber soft plate, the main body is annular, the inner circle is fixed on the outer wall of the accommodating shell 310, and the outer circle is fixed on the top of the tubular sac 351; the cross-section of the combination of the connecting soft plate 352 and the tubular sac 351 before the annular sac 353 expands is Inverted V shape; the annular capsule 353 is fixed on the outer wall of the accommodating shell 310 and is connected to the air chamber body 380. The valve body 390 is positioned on the connecting channel to control the opening and closing of the channel. The air chamber body 380 is filled with compressed gas. The operation of the valve body 390 is controlled by the control component 370 in the shell. The valve body 390 starts to operate after the parachute component 360 operates, and opens the channel to cause the annular capsule 353 to swell. The annular capsule 353 swells and squeezes the connecting soft plate 352 to cause the tubular capsule 351 to move down to cover the camera body 320, thereby protecting the camera body 320 from collision damage.

[0100] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. 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. A disposable independent monitoring camera for emergency situations of a flight training aircraft, characterized in that: It comprises a rotating column assembly (200), a camera assembly (300), a pulling rope assembly (400) and an ejection assembly (500); A passage (110) is provided near the top of the cabin shell (100), on which a sealing diaphragm (120) is fixed; the rotating column assembly (200) comprises a rotating column (210) and a support displacement assembly (220), and the rotating column (210) rotates under the drive of a column rotation drive assembly (230); The support displacement assembly (220) is a telescopic rod structure, fixed on the cabin shell (100), and used to drive the rotating column (210) to move relative to or towards each other, thereby timely clamping the pulling rope assembly (400); The camera assembly (300) comprises a housing (310) and a camera body (320); the housing (310) is a container; the camera body (320) is a ball head camera, fixed to the bottom of the housing (310); The pulling rope assembly (400) comprises a central rope (410), a hollow rod (420), a support frame (430), a retracting assembly (440) and a positioning frame assembly (460); the hollow rods (420) are multiple in number and are sleeved on the central rope (410); The retractable assembly (440) is a hoisting structure fixed on the supporting frame (430); One end of the central rope (410) is positioned on a positioning frame assembly (460) on the accommodating shell (310), and the other end is positioned on the retractable assembly (440); The ejection assembly (500) is used to eject the camera assembly (300) out of the training machine; The ejection assembly (500) comprises a limit frame (510), a sliding plate (520), a support rod (530), an energy storage compression spring (540) and a force storage assembly (550); The limit frame (510) is a frame structure, fixed on the cabin shell (100), located directly below the camera assembly (300), and used to limit the movement of the sliding plate (520), so that the sliding plate (520) can only move vertically upward or downward; The sliding plate (520) is slidably positioned on the limiting frame (510); The support rods (530) are arranged vertically, in multiple numbers, and one end away from the sliding plate (520) contacts the camera assembly (300); the energy storage compression spring (540) is positioned below the sliding plate (520) and is used to store and release elastic potential energy; The force storage component (550) is a hoisting structure, used to pull the sliding plate (520) downward to cause the energy storage compression spring (540) to accumulate elastic potential energy, and comprises a hoisting (551) and a hoisting rope (552); The hoist (551) is fixed to the bottom of the limit frame (510), one end of the hoist rope (552) is fixed to the hoist (551), and the other end is fixed to the sliding plate (520); when ejection is required, the hoist (551) releases the hoist rope (552), and the energy storage compression spring (540) releases the elastic potential energy.

2. The independent disposable monitoring camera for emergency state of flight training aircraft as claimed in claim 1, characterized in that: Also includes a protective capsule (350); The protective capsule (350) is fixed on the containing shell (310) to play a buffering role, thereby preventing the containing shell (310) from collision and damage; the protective capsule (350) is tubular and / or annular.

3. The independent disposable monitoring camera for emergency state of flight training aircraft according to claim 1 or 2, characterized in that: Also included is a detachable assembly, a parachute assembly (360) and an in-shell control assembly (370); The detaching component is positioned on the accommodating shell (310) and the positioning frame component (460) and is used to timely detach the accommodating shell (310) from the positioning frame component (460), and is a buckle, an electric heating body or an electric pin; The parachute assembly (360) is fixed on the housing (310) and is controlled by the in-shell control assembly (370) to operate; the in-shell control assembly (370) is connected to the training machine control unit by signal, is fixed inside the housing (310), and is used to control the detachment assembly and the parachute assembly (360) to operate in a timely manner.

4. The independent disposable monitoring camera for emergency state of flight training aircraft as claimed in claim 3, characterized in that: The control component (370) in the shell is electrically connected to the control unit of the training machine via a signal transmission line. The signal transmission lines are fixed on the central rope (410). There are two signal transmission lines. The two signal transmission lines are plugged together at the connection position between the housing (310) and the positioning frame component (460). The two signal transmission lines are disconnected when the housing (310) and the positioning frame component (460) are separated.

5. The independent disposable monitoring camera for emergency state of flight training aircraft as claimed in claim 2, characterized in that: The protective capsule (350) comprises a tubular capsule (351), a connecting soft plate (352) and an annular capsule (353); The accommodating shell (310) further includes an air chamber (380) and a valve body (390); The tubular capsule (351) is sleeved on the accommodating shell (310), and the inner circle diameter is larger than the circumscribed circle diameter of the accommodating shell (310); The connecting soft plate (352) is a soft plate made of rubber, and its main body is annular, with an inner ring fixed on the outer wall of the containing shell (310), and an outer ring fixed on the top of the tubular bag (351); The cross section of the assembly of the connecting soft plate (352) and the tubular bag (351) is an inverted V-shape before the annular bag body (353) expands; the annular bag body (353) is fixed on the outer wall of the accommodating shell (310) and communicates with the air chamber body (380); the valve body (390) is positioned on the communication channel to control the opening and closing of the channel; The air chamber (380) is filled with compressed gas; the operation of the valve body (390) is controlled by the control component (370) in the shell; The valve body (390) starts to operate after the parachute assembly (360) operates, opening the channel to cause the annular capsule (353) to expand, and the annular capsule (353) expands to squeeze the connecting soft plate (352) to cause the tubular capsule (351) to move downward to cover the camera body (320).

6. The independent disposable monitoring camera for emergency state of flight training aircraft as claimed in claim 1, characterized in that: The rotating column (210) comprises a column body (211) and a soft layer (212); The column (211) is a cylinder, and the soft layer (212) is a rubber tube with a thickness greater than 5 mm, which is coated on the side wall of the column (211) and is coaxial with the column (211).

7. The independent disposable monitoring camera for emergency state of flight training aircraft as claimed in claim 1, characterized in that: A hemispherical rod head convex block (421) is positioned at one end of the hollow rod (420), and a rod head concave pit (422) matched with the rod head convex block (421) is positioned at the other end.

8. The independent disposable monitoring camera for emergency state of flight training aircraft as claimed in claim 1, characterized in that: The central rope (410) comprises an elastic portion (411) and a non-elastic portion (412), wherein the elastic portion (411) is made of elastic rubber, and both the elastic portion (411) and the non-elastic portion (412) are rope bodies, which are alternately arranged and fixed together.

9. The independent disposable monitoring camera for emergency state of flight training aircraft as claimed in claim 3, characterized in that: The detachable component is a heating plate (470), which is an electric heating plate, electrically connected to the power supply component (330) in the shell and controlled by the control component (370) in the shell, and fixed at the connection position between the accommodating shell (310) and the positioning frame component (460), and the positioning frame component (460) is fixed to the accommodating shell (310) or the heating plate (470) by glue; when the heating plate (470) is heated up, the glue is rendered ineffective.

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