CN110816862A - Helicopter landing probe rod device and control method thereof - Google Patents
Helicopter landing probe rod device and control method thereof Download PDFInfo
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- CN110816862A CN110816862A CN201911228057.6A CN201911228057A CN110816862A CN 110816862 A CN110816862 A CN 110816862A CN 201911228057 A CN201911228057 A CN 201911228057A CN 110816862 A CN110816862 A CN 110816862A
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- probe
- probe rod
- linear motion
- rod body
- motion mechanism
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
Abstract
The invention belongs to an auxiliary landing system of a helicopter, and provides a landing probe device of the helicopter, which comprises a controller 101, a motor 102, a clutch 107, a linear motion mechanism 110, a probe rod and an elastic piece 109; the probe comprises a shell 103, a probe body 113 and a probe rod body 104, the shell 103 is fixed on the machine body structure 201, and the probe body 113 is slidably sleeved in the shell 103; the linear motion mechanism 110 penetrates through a through hole of the probe rod body 113 and is fixedly connected with the probe rod body 113; the elastic element 109 is sleeved outside the linear motion mechanism 110 and is located in the through hole of the probe rod body 113, and one end of the elastic element 109 is limited in the through hole of the probe rod body 113; one end of the probe rod body 104 is in contact with the other end of the elastic piece 109; when the probe rod body 104 retracts under a force, the elastic element 109 is compressed, and the probe rod body 104 is slidably sleeved outside the linear motion mechanism 110 and is located in the through hole of the probe rod body 113.
Description
Technical Field
The invention belongs to an auxiliary landing system of a helicopter, and particularly relates to a landing probe rod device of the helicopter and a control method thereof
Background
At present, carrier-based helicopter landing systems in the world mainly comprise a harpoon-grid landing system, an RAST pull-down system and an ASIST carrier-based helicopter comprehensive mooring and transportation system developed on the basis of the RAST pull-down system. The ASIST carrier-based helicopter comprehensive mooring and transporting system integrates functions required by helicopter landing and traction operation, and all ship surface operations can be completed without the need of workers on the scene of a flight deck.
The landing probe rod device is important equipment which is arranged on the ASIST carrier-borne helicopter in a comprehensive mooring and transferring system. The landing probe rod device is arranged under the belly of the helicopter, and the probe rod body part of the landing probe rod device can be retracted or released. When the helicopter is ready to land on a ship, the probe rod is released in advance, the control device on the ship tracks the probe rod of the helicopter and keeps a minimum safety distance, and once the carrier-based helicopter lands on the ship, the quick carrier surface mooring device quickly moves to the probe rod and captures the probe rod, so that the carrier-based helicopter is quickly moored on a flight deck. The existing carrier landing probe rod device cannot freely stretch out and draw back, and does not have a protection function when the compression amount of the probe rod is maximum.
Disclosure of Invention
The purpose of the invention is as follows: the invention relates to a helicopter landing probe device and a control method thereof, which are brand new research and development of a certain carrier-based helicopter auxiliary landing system.
The technical scheme of the invention is as follows: in one aspect, a landing probe device for a helicopter is provided, the landing probe device comprises a controller 101, a motor 102, a clutch 107, a linear motion mechanism 110, a probe rod and an elastic piece 109,
the controller 101 is electrically connected with the motor 102, and the controller 101 controls the motor 102 to work;
the output end of the motor 102 is connected with the clutch 107, and the clutch 107 is connected with the linear motion mechanism 110; the motor 102 drives the clutch 107 to drive the linear motion mechanism 110 to move in the vertical direction;
the probe comprises a shell 103, a probe body 113 and a probe rod body 104, the shell 103 is fixed on the machine body structure 201, and the probe body 113 is slidably sleeved in the shell 103; the linear motion mechanism 110 penetrates through a through hole of the probe rod body 113 and is fixedly connected with the probe rod body 113; the elastic element 109 is sleeved outside the linear motion mechanism 110 and is located in the through hole of the probe rod body 113, and one end of the elastic element 109 is limited in the through hole of the probe rod body 113;
one end of the probe rod body 104 is in contact with the other end of the elastic piece 109; when the probe rod body 104 is forced to retract, the elastic element 109 is compressed, and the probe rod body 104 is slidably sleeved outside the linear motion mechanism 110 and is positioned in the through hole of the probe rod body 113;
when the compression amount of the elastic member 109 is maximum, the clutch 107 is disconnected, and the probe body 113, the probe rod body 104 and the linear motion mechanism 110 move upward in the vertical direction.
Further, the landing probe rod device further comprises a hand-operated mechanism 108, the hand-operated mechanism 108 is connected with a linear motion mechanism 110, and the hand-operated mechanism 108 drives the linear motion mechanism 110 to move along the vertical direction.
Further, the landing probe device further comprises a potentiometer 105, wherein the potentiometer 105 is connected with the linear motion mechanism 110 and is used for monitoring the motion amount of the linear motion mechanism 110;
the potentiometer 105 is in signal connection with the controller 101 and is used for feeding back the movement amount of the linear movement mechanism 110 to the controller 101.
The landing probe rod device further comprises a speed reducer 106, an output end of the motor 102 is connected with an input end of the speed reducer 106, an output end of the speed reducer 106 is connected with a clutch 107, and the speed reducer 106 is used for reducing the rotating speed of an output shaft of the motor 102.
Further, the landing probe rod device further comprises a control switch, the control switch comprises a power switch and a probe rod retraction switch, and the power switch is electrically connected with the motor 102, the potentiometer 105 and the controller 101; the probe rod retracting switch is in signal connection with the controller 101, and the probe rod retracting switch is used for sending probe rod retracting or releasing signals to the controller 101.
Further, the landing probe rod device further comprises an indicator light, the indicator light is electrically connected with the controller 101, and the controller 101 controls the indicator light according to a feedback signal of the potentiometer 105.
Further, the probe rod further comprises an upper flange 111 and a lower flange 112, and the shell 103 of the probe rod is fixedly connected with the body structure 201 through the upper flange 111 and the lower flange 112;
the upper flange 111 and the shell 103 of the probe rod are of an integrated structure.
In another aspect, a helicopter landing probe control method is provided, which utilizes the helicopter landing probe device as described above, the method includes,
adjusting a power switch to be in a connection state, electrifying the controller 101 for self-checking, and feeding back fault information of the controller 101;
if the self-checking display controller 101 has faults, the hand-operated mechanism 108 is adopted to drive the linear motion mechanism 110 to move along the vertical direction;
if the self-checking display controller 101 is normal, the probe rod retracting switch is adjusted to the probe rod retracting position or the probe rod releasing position, the motor 102 drives the clutch 107 to drive the linear motion mechanism 110 to ascend or descend along the vertical direction, and the linear motion mechanism 110 drives the probe rod body 113 and the probe rod body 104 to ascend or descend along the vertical direction.
Further, when the probe rod retracting switch is adjusted to the releasing position, after the probe rod body 104 is in contact with the ground, the probe rod body 104 moves upwards along the vertical direction to compress the elastic piece 109, and the probe rod body 104 is slidably sleeved outside the linear motion mechanism 110 and is positioned in the through hole of the probe rod body 113;
when the compression amount of the elastic member 109 is maximum, the clutch 107 is disconnected, and the probe body 113, the probe rod body 104 and the linear motion mechanism 110 move upward in the vertical direction.
The invention has the beneficial effects that: the invention relates to an onboard component of a comprehensive mooring and transferring system of a carrier-based helicopter, which is a key component for rapid mooring and traction transfer when the helicopter lands on a ship. The adoption of the telescopic structure can reduce the aerodynamic resistance of the helicopter in flight, also can reduce the cantilever length of the probe rod body and improve the radial bearing capacity; by adopting the buffer spring and the overload clutch, the helicopter body structure can be effectively protected from being damaged in the process of landing the helicopter. The mounting structure of the upper flange and the lower flange is adopted, so that the mounting structure is simple and quick, and the transmission of radial and vertical loads is facilitated.
Drawings
Fig. 1 is a schematic view of a landing probe device and installation;
FIG. 2 is a schematic diagram of a control switch;
fig. 3 is a control flow chart of the landing probe device.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
Fig. 1 is a schematic view of a landing probe device and installation, and as shown in fig. 1, in this embodiment, a landing probe device for a helicopter is provided, which includes a controller 101, a motor 102, a clutch 107, a linear motion mechanism 110, a probe, and an elastic member 109,
the controller 101 is electrically connected with the motor 102, and the controller 101 controls the motor 102 to work;
the output end of the motor 102 is connected with the clutch 107, and the clutch 107 is connected with the linear motion mechanism 110; the motor 102 drives the clutch 107 to drive the linear motion mechanism 110 to move in the vertical direction;
the probe comprises a shell 103, a probe body 113 and a probe rod body 104, the shell 103 is fixed on the machine body structure 201, and the probe body 113 is slidably sleeved in the shell 103; the linear motion mechanism 110 penetrates through a through hole of the probe rod body 113 and is fixedly connected with the probe rod body 113; the elastic element 109 is sleeved outside the linear motion mechanism 110 and is located in the through hole of the probe rod body 113, and one end of the elastic element 109 is limited in the through hole of the probe rod body 113;
one end of the probe rod body 104 is in contact with the other end of the elastic piece 109; when the probe rod body 104 is forced to retract, the elastic element 109 is compressed, and the probe rod body 104 is slidably sleeved outside the linear motion mechanism 110 and is positioned in the through hole of the probe rod body 113;
when the compression amount of the elastic member 109 is maximum, the clutch 107 is disconnected, and the probe body 113, the probe rod body 104 and the linear motion mechanism 110 move upward in the vertical direction.
The adoption of the telescopic structure can reduce the aerodynamic resistance of the helicopter in flight, also can reduce the cantilever length of the probe rod body and improve the radial bearing capacity; by adopting the buffer spring and the overload clutch, the helicopter body structure can be effectively protected from being damaged in the process of landing the helicopter.
Further, the landing probe rod device further comprises a hand-operated mechanism 108, the hand-operated mechanism 108 is connected with a linear motion mechanism 110, and the hand-operated mechanism 108 drives the linear motion mechanism 110 to move along the vertical direction.
The probe rod device of the embodiment is normally controlled to be retracted and retracted through electricity, and is retracted and retracted through manual machinery under the condition that the electricity is failed to retract and retract.
Further, the landing probe device further comprises a potentiometer 105, wherein the potentiometer 105 is connected with the linear motion mechanism 110 and is used for monitoring the motion amount of the linear motion mechanism 110; the potentiometer 105 is in signal connection with the controller 101 and is used for feeding back the movement amount of the linear movement mechanism 110 to the controller 101.
Further, the landing probe device further comprises a speed reducer 106, an output end of the motor 102 is connected with an input end of the speed reducer 106, an output end of the speed reducer 106 is connected with a clutch 107, and the speed reducer 106 is used for reducing the rotating speed of an output shaft of the motor 102.
FIG. 2 is a schematic diagram of a control switch; as shown in fig. 1 and fig. 2, the landing probe device further includes a control switch, where the control switch includes a power switch and a probe retraction switch, and the power switch is electrically connected to the motor 102, the potentiometer 105, and the controller 101; the probe rod retracting switch is in signal connection with the controller 101, and the probe rod retracting switch is used for sending probe rod retracting or releasing signals to the controller 101.
Further, the landing probe rod device further comprises an indicator light, the indicator light is electrically connected with the controller 101, and the controller 101 controls the indicator light according to a feedback signal of the potentiometer 105.
Further, the probe rod further comprises an upper flange 111 and a lower flange 112, and the shell 103 of the probe rod is fixedly connected with the body structure 201 through the upper flange 111 and the lower flange 112; the upper flange 111 and the shell 103 of the probe rod are of an integrated structure. The upper flange of the warship landing probe rod device is designed to be integrated with the probe rod shell, the upper flange is limited through two limiting blocks on the web upper panel, the lower flange is of a detachable structure, and the lower flange is in threaded connection with the probe rod shell, so that the warship landing probe rod device can be rapidly installed and detached on a machine conveniently.
The landing probe rod device has the functions of power-on self-inspection, position detection, position feedback, fault alarm, probe rod retraction and extension frequency statistics, probe rod retraction and extension controlled electrically and manually and the like.
Example 2
The embodiment provides a control method of a landing probe of a helicopter, which utilizes the landing probe device of the helicopter, and the method comprises the following steps,
adjusting a power switch to be in a connection state, electrifying the controller 101 for self-checking, and feeding back fault information of the controller 101;
if the self-checking display controller 101 has faults, the hand-operated mechanism 108 is adopted to drive the linear motion mechanism 110 to move along the vertical direction;
if the self-checking display controller 101 is normal, the probe rod retracting switch is adjusted to the probe rod retracting position or the probe rod releasing position, the motor 102 drives the clutch 107 to drive the linear motion mechanism 110 to ascend or descend along the vertical direction, and the linear motion mechanism 110 drives the probe rod body 113 and the probe rod body 104 to ascend or descend along the vertical direction.
Further, when the probe rod retracting switch is adjusted to the releasing position, after the probe rod body 104 is in contact with the ground, the probe rod body 104 moves upwards along the vertical direction to compress the elastic piece 109, and the probe rod body 104 is slidably sleeved outside the linear motion mechanism 110 and is positioned in the through hole of the probe rod body 113;
when the compression amount of the elastic member 109 is maximum, the clutch 107 is disconnected, and the probe body 113, the probe rod body 104 and the linear motion mechanism 110 move upward in the vertical direction.
When the interference amount of the ship deck to the probe rod is small, the buffer spring is used for buffering, when the interference amount of the ship deck to the probe rod is large, and the stroke of the buffer spring is used up, the clutch in the probe rod device is automatically disengaged, and the probe rod can continuously retract, so that the probe rod device and the machine body structure are prevented from being damaged. When the power-on self-checking fault or the electrical control retraction fault occurs in the warship landing probe rod device, an alarm signal can be given to the cockpit, so that a pilot can know the retraction condition of the probe rod and can perform emergency manual retraction in time.
Example 3
With reference to fig. 3, fig. 3 is a control flow chart of the landing probe device, and with reference to fig. 1, fig. 2 and fig. 3, the practical control principle of the present invention is as follows.
A. Method for electrically controlling discharge
1) And (3) placing a power switch on the landing control panel at a 'switch-on' position, and electrifying the landing probe rod device for self-detection. And if the fault is detected, sending fault information to a helicopter electromechanical management system, and displaying the fault of the landing feeler lever device by the helicopter electromechanical management system, wherein at the moment, only emergency manual releasing operation can be used.
2) Under the normal condition of circular telegram self-checking, will land on the warship the control panel "probe rod receive and release switch" switch and place "play" position in, "the probe rod moves and emits, and after the probe rod emitted and target in place, the pilot lamp lighted, and this embodiment pilot lamp can be for" the probe rod emits "lamp. If the feeler lever goes out of order, the indicator light is not on, and the electromechanical management system of the helicopter displays 'the failure of the landing feeler lever device', at the moment, only emergency manual release operation can be used.
3) And (4) placing the landing power switch at an 'off' position to disconnect the power supply.
B. Method for electrically controlling retraction
1) And (3) placing a landing power switch on the landing control panel at a 'switch-on' position, and electrifying the landing probe rod device for self-detection. And if the fault is detected, sending fault information to a helicopter electromechanical management system, and displaying the fault of the landing feeler lever device by the helicopter electromechanical management system, wherein at the moment, only emergency manual releasing operation can be used.
2) Under the condition that the power-on self-inspection is normal, a probe rod retraction switch on the landing control plate is arranged at a retraction position, the probe rod is actuated to retract, and after the probe rod is retracted to the proper position, the indicator lamp is turned off, namely, the probe rod emitting lamp is turned off. If the probe rod breaks down in the retraction process, the lamp which is released by the probe rod is not extinguished, the electromechanical management system of the helicopter displays that the landing probe rod device breaks down, and at the moment, only emergency manual retraction operation can be used.
3) The power switch of the landing ship power supply is arranged at an off position, and the power supply is disconnected.
C. Emergency manual discharge operation method
1) When the power-on self-checking fault or the electrical control releasing fault occurs in the ship landing probe rod device;
2) and rotating a manual handle on the landing probe rod device in the probe rod releasing direction, and after the probe rod is released in place, lighting a probe rod releasing lamp.
3) The power switch of the landing ship power supply is arranged at an off position, and the power supply is disconnected.
D. Operation method for emergency manual retraction
1) When the ship landing probe rod device has a power-on self-detection fault or an electrical control retraction fault;
2) and rotating a manual handle on the warship landing probe rod device in the probe rod retracting direction, and after the probe rod is retracted in place, turning off a lamp emitted by the probe rod.
3) The power switch of the landing ship power supply is arranged at an off position, and the power supply is disconnected.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. A helicopter landing probe device is characterized by comprising a controller (101), a motor (102), a clutch (107), a linear motion mechanism (110), a probe and an elastic piece (109),
the controller (101) is electrically connected with the motor (102), and the controller (101) controls the motor (102) to work;
the output end of the motor (102) is connected with the clutch (107), and the clutch (107) is connected with the linear motion mechanism (110); the motor (102) drives the clutch (107) to drive the linear motion mechanism (110) to move along the vertical direction;
the probe comprises a shell (103), a probe body (113) and a probe rod body (104), the shell (103) is fixed on a machine body structure (201), and the probe body (113) is slidably sleeved in the shell (103); the linear motion mechanism (110) penetrates through the through hole of the probe rod body (113) and is fixedly connected with the probe rod body (113); the elastic piece (109) is sleeved outside the linear motion mechanism (110) and is positioned in the through hole of the probe rod body (113), and one end of the elastic piece (109) is limited in the through hole of the probe rod body (113);
one end of the probe rod body (104) is contacted with the other end of the elastic piece (109); when the probe rod body (104) is stressed to retract, the elastic piece (109) is compressed, and the probe rod body (104) is slidably sleeved outside the linear motion mechanism (110) and is positioned in the through hole of the probe rod body (113);
when the compression amount of the elastic piece (109) is maximum, the clutch (107) is disconnected, and the probe rod body (113), the probe rod body (104) and the linear motion mechanism (110) move upwards along the vertical direction.
2. The helicopter landing probe device according to claim 1, characterized by that, the landing probe device further comprises a hand-operated mechanism (108), the hand-operated mechanism (108) is connected with the linear motion mechanism (110), and the hand-operated mechanism (108) drives the linear motion mechanism (110) to move along the vertical direction.
3. The helicopter landing probe device of claim 1, further comprising a speed reducer (106), wherein the output end of the motor (102) is connected to the input end of the speed reducer (106), the output end of the speed reducer (106) is connected to a clutch (107), and the speed reducer (106) is used for reducing the rotation speed of the output shaft of the motor (102).
4. The helicopter landing probe device of claim 1, further comprising a potentiometer (105), wherein the potentiometer (105) is connected to the linear motion mechanism (110) for monitoring the amount of motion of the linear motion mechanism (110);
the potentiometer (105) is in signal connection with the controller (101) and is used for feeding back the movement amount of the linear motion mechanism (110) to the controller (101).
5. The helicopter landing probe device of claim 4, further comprising a control switch, wherein the control switch comprises a power switch and a probe retraction switch, and the power switch is electrically connected with the motor (102), the potentiometer (105) and the controller (101); the probe rod retracting switch is in signal connection with the controller (101), and the probe rod retracting switch is used for sending probe rod retracting or releasing signals to the controller (101).
6. The helicopter landing probe device of claim 5, further comprising an indicator light electrically connected to the controller (101), wherein the controller (101) controls the indicator light based on a feedback signal from the potentiometer (105).
7. The helicopter landing probe device of claim 1, wherein the probe further comprises an upper flange (111) and a lower flange (112), and the housing (103) of the probe is fixedly connected with the airframe structure (201) through the upper flange (111) and the lower flange (112);
the upper flange (111) and the shell (103) of the probe rod are of an integrated structure.
8. A helicopter landing probe control method, which utilizes the helicopter landing probe device as claimed in any one of claims 1 to 7, characterized in that the method comprises,
adjusting a power switch to be in a connection state, enabling the controller (101) to be electrified for self-checking, and feeding back fault information of the controller (101);
if the self-checking display controller (101) fails, a hand-operated mechanism (108) is adopted to drive the linear motion mechanism (110) to move along the vertical direction;
if the self-checking display controller (101) is normal, the probe rod retracting switch is adjusted to a probe rod retracting position or a probe rod releasing position, the motor (102) drives the clutch (107) to drive the linear motion mechanism (110) to ascend or descend along the vertical direction, and the linear motion mechanism (110) drives the probe rod body (113) and the probe rod body (104) to ascend or descend along the vertical direction.
9. The helicopter landing probe control method of claim 8, comprising,
when the probe rod retraction switch is adjusted to the release position, the probe rod body (104) moves upwards along the vertical direction after contacting the ground or the ship deck, and the elastic piece (109) is compressed; the probe rod body (104) is slidably sleeved outside the linear motion mechanism (110) and is positioned in a through hole of the probe rod body (113);
when the compression amount of the elastic piece (109) is maximum, the clutch (107) is disconnected, and the probe rod body (113), the probe rod body (104) and the linear motion mechanism (110) move upwards along the vertical direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911228057.6A CN110816862B (en) | 2019-12-04 | 2019-12-04 | Helicopter carrier landing feeler lever device and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911228057.6A CN110816862B (en) | 2019-12-04 | 2019-12-04 | Helicopter carrier landing feeler lever device and control method thereof |
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| Publication Number | Publication Date |
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| CN110816862A true CN110816862A (en) | 2020-02-21 |
| CN110816862B CN110816862B (en) | 2022-09-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911228057.6A Active CN110816862B (en) | 2019-12-04 | 2019-12-04 | Helicopter carrier landing feeler lever device and control method thereof |
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