CN113928577A - Helicopter emergency buffering landing device - Google Patents
Helicopter emergency buffering landing device Download PDFInfo
- Publication number
- CN113928577A CN113928577A CN202111381949.7A CN202111381949A CN113928577A CN 113928577 A CN113928577 A CN 113928577A CN 202111381949 A CN202111381949 A CN 202111381949A CN 113928577 A CN113928577 A CN 113928577A
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- helicopter
- explosive
- buffer
- explosion
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- 230000003139 buffering effect Effects 0.000 title claims abstract description 11
- 238000004880 explosion Methods 0.000 claims abstract description 34
- 239000002360 explosive Substances 0.000 claims abstract description 27
- 238000002955 isolation Methods 0.000 claims abstract description 21
- 230000002441 reversible effect Effects 0.000 claims abstract description 16
- 239000002184 metal Substances 0.000 claims description 14
- 210000001015 abdomen Anatomy 0.000 claims description 10
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 230000001960 triggered effect Effects 0.000 claims description 4
- 238000000034 method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 239000003721 gunpowder Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Vibration Dampers (AREA)
Abstract
The invention provides an emergency buffer landing device of a helicopter, which comprises: the explosion device is arranged in the isolation device and is used for generating reverse action impulse; the buffer device is arranged on the explosion device and used for buffering the reverse acting impulse; an isolation device for preventing said explosive device from damaging the helicopter; the control device is electrically connected with the explosion device and used for controlling the explosion device; the high-energy explosive can generate a large amount of energy, the reverse acting force acts on the main bearing structure of the helicopter body through the buffer device, the grounding speed of the helicopter can be reduced, the helicopter is grounded at a low speed, and the use safety of the helicopter in emergency situations such as main propellers or tail rotor vortex rings, tail rotors or engine failure and the like is effectively improved.
Description
Technical Field
The invention belongs to the technical field of helicopter flight safety, and particularly relates to a helicopter emergency buffering landing device.
Background
Factors influencing safe flight of the helicopter are many, such as improper operation and easy entry of a main rotor or a tail rotor vortex ring, which is a dangerous special flight state, and accidents are caused at home and abroad; when the engine fails or the tail rotor fails, the helicopter needs to immediately rotate, the time left for a pilot to handle is very short, and the helicopter is extremely easy to cause overlarge ground speed and casualties.
The invention provides a helicopter emergency buffer landing method and device by utilizing gunpowder explosion reverse impulse, aiming at the fault conditions of a main propeller vortex ring, a tail propeller vortex ring or a key system of a helicopter, and the helicopter emergency buffer landing method and device can slow down the grounding speed of a helicopter and improve the flight safety of the helicopter.
Disclosure of Invention
In view of the above technical problems, the present invention provides an emergency buffer landing device for a helicopter, comprising:
the explosion device is arranged in the isolation device and is used for generating reverse action impulse;
the buffer device is arranged on the explosion device and used for buffering the reverse acting impulse;
an isolation device for preventing said explosive device from damaging the helicopter;
and the control device is electrically connected with the explosion device and used for controlling the explosion device.
Preferably, the explosive device comprises: the explosive-free metal block comprises a metal block, a belly body, a punch, an explosive, an ignition device, a sub-buffer device and a connecting device.
Preferably, the metal block is arranged in the belly, a punch is arranged above the belly, an explosive is arranged above the punch, and the explosive is connected with the ignition device.
Preferably, the buffering means comprises: the device comprises a main spring, a secondary spring, a base plate and a mass block;
wherein the primary spring and the secondary spring are disposed between the backing plate and the mass.
Preferably, the main spring is arranged in the middle of the backing plate, and the secondary springs are symmetrically arranged on two sides of the main spring.
Preferably, the isolation device is made of high strength isolation metal steel.
Preferably, the control device includes:
the cockpit control button is arranged in the error-proof protection box;
the error-proof protection box is used for protecting the control button of the cockpit from being triggered by mistake; wherein the cockpit control button is connected with the explosive device through a wire.
Preferably, the method further comprises the following steps:
and the connecting bottom plate is arranged at the port of the isolating device.
The invention has the beneficial technical effects that:
the invention provides a helicopter emergency buffering landing method and a device thereof, wherein before a system fault or emergency landing such as a vortex ring, a pilot connects an explosive device to detonate the explosive device, a large amount of energy can be generated due to a small amount of weight of high-energy explosive, and reverse acting force acts on a main bearing structure of a fuselage through a buffer device, so that the grounding speed of the helicopter can be reduced, the helicopter is grounded at a low speed, and the use safety of the helicopter in emergency situations such as main rotor or tail rotor vortex ring, tail rotor or engine failure is effectively improved.
Drawings
Fig. 1 is a schematic structural diagram of an explosive device provided by an embodiment of the invention;
FIG. 2 is a schematic structural diagram of a buffering device according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of an onboard installation provided by an embodiment of the present invention;
wherein: 1-metal block, 2-belly, 3-punch, 4-explosive, 5-ignition device, 6-sub-buffer device, 7-cover plate, 8-backing plate, 9-main spring, 10-secondary spring, 11-mass block, 12-button, 13-error-proof box, 14-wire, 15-connecting bottom plate, 16-buffer device, 17-explosion device and 18-isolation device.
Detailed Description
When a helicopter flies, under the condition that a main rotor vortex ring, a tail rotor vortex ring or a key system fails, the helicopter slides downwards, and the vertical grounding speed of the helicopter exceeds the limit, so that the damage to helicopter system equipment or the casualties are caused. Referring to fig. 1-3, the invention provides an emergency buffer landing device for a helicopter, which provides a reverse impulse by powder explosion, and has a low weight cost, and can effectively slow down the vertical grounding speed of the helicopter, realize safe landing and improve the flight safety of the helicopter.
The invention provides an emergency buffer landing device for a helicopter, which comprises four parts, namely an explosion device 17, a buffer device 16, an isolation device 18 and a control device; furthermore, a connection base plate 15 is included.
The explosion device comprises 7 parts, namely a metal block 1, a belly 2, a punch 3, an explosive 4, an ignition device 5, a sub-buffer device 6, a connecting device and the like;
the buffer device 16 comprises 1 main spring 9, 2 secondary springs 10, a backing plate 8 and a mass block 11; the isolation device 18 is made of high-strength isolation metal steel; the control means comprise a cockpit control button 12, an error protection box 13 and a wire 14.
In the embodiment of the application, the belly body of the explosive device must have enough length to ensure enough action distance during explosion, and the explosive amount can be calculated according to the impulse reduced as required.
The springs and the mass blocks with different rigidity and damping coefficients are adopted, so that the action time of gunpowder on the helicopter body during launching can be prolonged, and the direct impact on the helicopter body structure is reduced. The isolating device is made of high-strength metal steel and is in a circular arc shape, so that stress concentration is avoided. Through the wire, the pilot can directly trigger the explosive device in the cockpit, set up switch protection device.
Wherein, under the cabin floor (course corresponds to the main reducing position) corresponding to the position of the rotor shaft, local structure strengthening is carried out on the frame beam, a buffer device is installed, and then the isolation device is connected with the explosion device.
The invention provides a helicopter emergency buffering landing device utilizing gunpowder explosion reverse impulse, which has low weight cost and can effectively slow down the vertical grounding speed of a helicopter, and the basic principle is as follows:
when the helicopter engine fails or the tail rotor fails, the helicopter is in a fault state, the grounding speed is high, and according to a formula: i ═ m.v (1)
The impulse of the helicopter in the direction vertical to the ground is equal to the mass multiplied by the speed, in order to reduce the grounding speed, reverse acting force, namely upward force is needed, when an engine fails or emergency conditions such as a vortex ring state and the like exist, a rotor wing can not provide enough lift force, an external force is needed, when the helicopter is in the air, the speed of the helicopter can be reduced by transmitting the reverse impulse through a substance, when an emergency buffer device on the helicopter explodes, the substance is transmitted downwards, and the upward impulse is generated due to the action of the reverse force according to a formula (1)
I1-ΔI＝m·v1-m·v2 (2)
I1-ΔI＝m(v1-v2) (3)
Thus reducing the speed
Δγ＝(I1-ΔI)/m (4)
Based on the principle, the core device of the technical scheme of the invention is an explosion device, directly provides reverse impulse, and additionally comprises a buffer device, an isolating device, a control device and the like in order to prevent impact load from exceeding the structural limit and facilitate the triggering of a pilot before landing.
The core device of the technical scheme of the invention is an explosion device, and the explosion device further comprises four main components of a buffer device, an isolation device and a control device.
The invention constitutes a core explosion device: mainly comprises a metal block, a belly, a punch, explosive, an ignition device, a buffer device and a connecting device.
The second component is a buffer device, except the buffer device of the explosion device, the buffer device is also needed, the impulse of explosion reduction is smoothly transmitted to the machine body, and the second component mainly comprises a mass block, a secondary spring, a base plate and a main spring.
The third component is an isolation device, an isolation system is needed, the safety of the helicopter can be guaranteed when the explosion device is triggered by mistake, and the third component is made of high-strength materials and designed into a cylinder.
The control system and the protection device comprise a control button of the cockpit, an error-proof protection box and a lead, and when the cockpit has an emergency situation, a pilot can directly trigger the ignition device.
The whole system is characterized in that local structure reinforcement is carried out on a frame beam below a cabin floor (the course corresponds to a main reducing position), a buffer device is installed, an isolation device is connected with an explosion device, and the whole device is connected with a structure.
The invention provides a helicopter emergency buffering landing method and a device thereof, wherein before a system fault or emergency landing such as a vortex ring, a pilot connects an explosive device to detonate the explosive device, a large amount of energy can be generated due to a small amount of weight of high-energy explosive, and reverse acting force acts on a main bearing structure of a fuselage through a buffer device, so that the grounding speed of the helicopter can be reduced, the helicopter is grounded at a low speed, and the use safety of the helicopter in emergency situations such as main rotor or tail rotor vortex ring, tail rotor or engine failure is effectively improved.
The helicopter emergency buffer landing device related to the invention is further described in detail with reference to the attached drawings 1-3.
The device comprises four parts, namely an explosion device, a buffer device, an isolating device and a control device.
The core explosion device of the invention: mainly comprises a metal block, a belly body, a punch, explosive, an ignition device, a buffer device and a connecting device, and is shown in figure 1.
The buffer device is needed besides the buffer device of the explosion device, the impulse of explosion reduction is smoothly transmitted to the machine body, and the buffer device mainly comprises a mass block, a spring, a bottom plate and a main spring.
The isolation device needs an isolation system, when the explosion device is triggered by mistake, the safety of the helicopter can be ensured, high-strength materials are adopted, and the design of the cylinder is shown in figure 3.
The control system and the protection device comprise a control button of the cockpit, an error-proof protection box and a lead, specifically shown in figure 3, when the cockpit has an emergency, the pilot can directly trigger the ignition device
Under the cabin floor (the course corresponds to the main reducing position), local structure reinforcement is carried out on the frame beam, a buffer device is installed, the isolation device is connected with the explosion device, and the whole device connecting structure is shown in figure 3.
Claims (8)
1. An emergency buffer landing device for a helicopter, comprising:
the explosion device is arranged in the isolation device and is used for generating reverse action impulse;
the buffer device is arranged on the explosion device and used for buffering the reverse acting impulse;
an isolation device for preventing said explosive device from damaging the helicopter;
and the control device is electrically connected with the explosion device and used for controlling the explosion device.
2. A helicopter emergency buffer landing gear according to claim 1, wherein said explosive device comprises: the explosive-free metal block comprises a metal block, a belly body, a punch, an explosive, an ignition device, a sub-buffer device and a connecting device.
3. A helicopter emergency buffer landing gear according to claim 2, wherein said metal block is disposed within said belly, a ram is disposed above said belly, and an explosive charge is disposed above said ram and is connected to said ignition device.
4. A helicopter emergency buffer landing gear according to claim 3, wherein said buffer means comprises: the device comprises a main spring, a secondary spring, a base plate and a mass block;
wherein the primary spring and the secondary spring are disposed between the backing plate and the mass.
5. A helicopter emergency buffer landing gear according to claim 4, wherein said primary spring is disposed in the middle of said pad and said secondary springs are symmetrically disposed on either side of said primary spring.
6. A helicopter emergency buffer landing gear according to claim 1, wherein said isolation means is made of a high strength isolating metal steel.
7. A helicopter emergency buffer landing gear according to claim 1, wherein said control means comprises:
the cockpit control button is arranged in the error-proof protection box;
the error-proof protection box is used for protecting the control button of the cockpit from being triggered by mistake; wherein the cockpit control button is connected with the explosive device through a wire.
8. A helicopter emergency buffer landing gear according to claim 1, further comprising:
and the connecting bottom plate is arranged at the port of the isolating device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111381949.7A CN113928577B (en) | 2021-11-19 | 2021-11-19 | Emergent buffering landing gear of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111381949.7A CN113928577B (en) | 2021-11-19 | 2021-11-19 | Emergent buffering landing gear of helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113928577A true CN113928577A (en) | 2022-01-14 |
| CN113928577B CN113928577B (en) | 2023-10-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111381949.7A Active CN113928577B (en) | 2021-11-19 | 2021-11-19 | Emergent buffering landing gear of helicopter |
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| Country | Link |
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| CN (1) | CN113928577B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4676457A (en) * | 1984-06-21 | 1987-06-30 | Allen Sebree J | Aircraft emergency landing system |
| JPH08192797A (en) * | 1995-01-19 | 1996-07-30 | Ayako Otsuka | Safety helicopter |
| US6371410B1 (en) * | 2000-09-28 | 2002-04-16 | The United States Of America Represented By The Secretary Of The Navy | Emergency landing impact absorbing system for aircraft |
| RU2232698C1 (en) * | 2002-12-23 | 2004-07-20 | Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" | Ejection unit for emergency rescue of pilot |
| CN203753412U (en) * | 2014-03-03 | 2014-08-06 | 浙江大学 | Out-of-control falling protection device of rotary wing type unmanned aerial vehicle |
| CN111470036A (en) * | 2020-04-30 | 2020-07-31 | 中国飞机强度研究所 | Anti single leg buffer structure and leg formula undercarriage that hit that weigh down |
| CN111470035A (en) * | 2020-04-30 | 2020-07-31 | 中国飞机强度研究所 | Complex terrain self-adaptive landing gear of vertical take-off and landing aircraft and landing method thereof |
| CN112173143A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Emergency substitution device for helicopter tail rotor in failure state and control method |
-
2021
- 2021-11-19 CN CN202111381949.7A patent/CN113928577B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4676457A (en) * | 1984-06-21 | 1987-06-30 | Allen Sebree J | Aircraft emergency landing system |
| JPH08192797A (en) * | 1995-01-19 | 1996-07-30 | Ayako Otsuka | Safety helicopter |
| US6371410B1 (en) * | 2000-09-28 | 2002-04-16 | The United States Of America Represented By The Secretary Of The Navy | Emergency landing impact absorbing system for aircraft |
| RU2232698C1 (en) * | 2002-12-23 | 2004-07-20 | Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" | Ejection unit for emergency rescue of pilot |
| CN203753412U (en) * | 2014-03-03 | 2014-08-06 | 浙江大学 | Out-of-control falling protection device of rotary wing type unmanned aerial vehicle |
| CN111470036A (en) * | 2020-04-30 | 2020-07-31 | 中国飞机强度研究所 | Anti single leg buffer structure and leg formula undercarriage that hit that weigh down |
| CN111470035A (en) * | 2020-04-30 | 2020-07-31 | 中国飞机强度研究所 | Complex terrain self-adaptive landing gear of vertical take-off and landing aircraft and landing method thereof |
| CN112173143A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Emergency substitution device for helicopter tail rotor in failure state and control method |
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| Publication number | Publication date |
|---|---|
| CN113928577B (en) | 2023-10-27 |
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