CN113928577B - Emergent buffering landing gear of helicopter - Google Patents
Emergent buffering landing gear of helicopter Download PDFInfo
- Publication number
- CN113928577B CN113928577B CN202111381949.7A CN202111381949A CN113928577B CN 113928577 B CN113928577 B CN 113928577B CN 202111381949 A CN202111381949 A CN 202111381949A CN 113928577 B CN113928577 B CN 113928577B
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- helicopter
- buffer
- explosive
- explosion
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- 230000003139 buffering effect Effects 0.000 title claims abstract description 5
- 238000004880 explosion Methods 0.000 claims abstract description 35
- 239000002360 explosive Substances 0.000 claims abstract description 24
- 238000002955 isolation Methods 0.000 claims abstract description 21
- 239000002184 metal Substances 0.000 claims description 12
- 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
- 239000003721 gunpowder Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000000463 material Substances 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
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
Classifications
-
- 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)
- Vibration Dampers (AREA)
- Toys (AREA)
Abstract
The application provides an emergency buffer landing device of a helicopter, which comprises: an explosive device disposed within the isolation device for generating a reverse acting impulse; a buffer device disposed on the explosive device for buffering the reverse-acting impulse; an isolation device for preventing damage to the helicopter by the explosive device; the control device is electrically connected with the explosion device and is 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, so that the grounding speed of the helicopter can be slowed down, the low-speed grounding of the helicopter is realized, and the use safety of the helicopter in emergency situations such as failure of a main propeller or a tail propeller vortex ring, a tail propeller or an engine and the like is effectively improved.
Description
Technical Field
The application belongs to the technical field of helicopter flight safety, and particularly relates to an emergency buffer landing device of a helicopter.
Background
Factors influencing the safe flight of a helicopter are many, such as a main propeller or a tail rotor vortex ring which is easy to enter due to improper control, and the helicopter is in a dangerous special flight state, and accidents occur at home and abroad; when the engine fails or the tail rotor fails, the helicopter needs to immediately enter autorotation, the disposal time for a pilot is very short, and the ground speed of the helicopter is very easy to be excessively high, so that the personnel are injured.
Aiming at the fault condition of a main rotor vortex ring, a tail rotor vortex ring or a key system of the helicopter, the application provides the helicopter emergency buffer landing method and device by utilizing the reverse impulse of gunpowder explosion, which can slow down the grounding speed of the helicopter and improve the flight safety of the helicopter.
Disclosure of Invention
Aiming at the technical problems, the application provides an emergency buffer landing device of a helicopter, which comprises:
an explosive device disposed within the isolation device for generating a reverse acting impulse;
a buffer device disposed on the explosive device for buffering the reverse-acting impulse;
an isolation device for preventing damage to the helicopter by the explosive device;
and the control device is electrically connected with the explosion device and is used for controlling the explosion device.
Preferably, the explosive device comprises: the device comprises a metal block, a belly body, a punch, an explosive, an ignition device, a sub-buffering device and a connecting device.
Preferably, the metal block is arranged in the abdomen body, a punch is arranged above the abdomen body, and an explosive is arranged above the punch and is connected with the ignition device.
Preferably, the buffer device comprises: the device comprises a main spring, a secondary spring, a backing 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 base 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 protection box;
the error protection box is used for protecting the control button of the cockpit from being triggered by errors; wherein, cockpit control button passes through the wire with explosion device connects.
Preferably, the method further comprises:
and the connecting bottom plate is arranged at the port of the isolating device.
The beneficial technical effects of the application are as follows:
the application provides an emergency buffer landing method and device for a helicopter, wherein a pilot is connected with an explosion device to detonate the explosion device before system faults or vortex rings and other emergency landings, and a large amount of energy can be generated due to the small weight of high-energy explosive, and reverse acting force acts on a main bearing structure of a helicopter body through the buffer device, so that the grounding speed of the helicopter can be slowed down, the small-speed grounding of the helicopter can be realized, and the use safety of the helicopter in emergency situations such as failure of a main propeller or a tail propeller or an engine is effectively improved.
Drawings
FIG. 1 is a schematic view of an explosive device according to an embodiment of the present application;
FIG. 2 is a schematic diagram of a buffer device according to an embodiment of the present application;
FIG. 3 is a schematic illustration of an on-board installation provided by an embodiment of the present application;
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 protection box, 14-wire, 15-connection base plate, 16-buffer device, 17-explosion device and 18-isolation device.
Detailed Description
Aiming at the condition that a main propeller vortex ring, a tail propeller vortex ring or a key system fails when the helicopter flies, the helicopter slides downwards, and the vertical grounding speed often exceeds the limit, so that the helicopter system equipment is damaged or casualties are caused. Referring to fig. 1-3, the application provides an emergency buffer landing device for a helicopter, which provides reverse impulse by utilizing gunpowder explosion, has low weight cost, can effectively slow down the vertical grounding speed of the helicopter, realizes safe landing and improves the flight safety of the helicopter.
The application provides an emergency buffer landing device of a helicopter, which comprises four parts, namely an explosion device 17, a buffer device 16, an isolation device 18 and a control device; further, a connection base 15 is included.
The explosion device comprises 7 parts, namely a metal block 1, a belly body 2, a punch 3, explosive 4, an ignition device 5, a sub-buffer device 6, a connecting device and the like;
wherein the buffer device 16 comprises 1 main spring 9, 2 secondary springs 10, a backing plate 8 and a mass block 11; the isolating device 18 is made of high-strength isolating metal steel; the control means comprise a cockpit control button 12, a fault protection box 13 and wires 14.
In the embodiment of the application, the belly of the explosion device must have a sufficient length to ensure a sufficient working distance during explosion, and in addition, the explosive amount can be calculated according to the impulse which is reduced according to the requirement.
The springs and the mass blocks with different rigidities and damping coefficients are adopted, so that the action time of gunpowder on the helicopter body during emission can be prolonged, and the direct impact on the helicopter body structure can be reduced. The isolating device is made of high-strength metal steel and is arc-shaped, so that stress concentration is avoided. Through the wire, the pilot can directly trigger the explosion device in the cockpit, sets up switch protection device.
And the frame beam is locally structurally reinforced under the cabin floor corresponding to the rotor shaft position (the heading corresponds to the main subtracting position), a buffer device is arranged, and then the isolation device is connected with the explosion device.
The application provides a helicopter emergency buffer landing device utilizing gunpowder explosion reverse impulse, which has low weight cost, can effectively slow down the vertical grounding speed of a helicopter, and has the following basic principle:
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 the formula: i=m·v (1)
The impulse in the vertical ground direction of the helicopter is equal to the mass multiplied by the speed, in order to reduce the ground speed, a reverse acting force, namely an upward force, is required, when the engine fails or the emergency conditions such as the vortex ring state and the like are met, the rotor cannot provide enough lifting force, the external force is required, when the helicopter is in the air, the speed of the helicopter can be reduced by the impulse emitted by the substance in the reverse direction, when the emergency buffer device on the helicopter explodes, the substance emits downwards, and the upward impulse is generated due to the action of the reverse force, and is shown as a formula (1)
I 1 -ΔI＝m·v 1 -m·v 2 (2)
I 1 -ΔI＝m(v 1 -v 2 ) (3)
Thus reducing the speed
Δ γ ＝(I 1 -ΔI)/m (4)
Based on the principle, the core device of the technical scheme is an explosion device, directly provides reverse impulse, is convenient for a pilot to trigger before landing in order to prevent impact load from exceeding structural limit, and also comprises a buffer device, an isolation device, a control device and the like.
The core device of the technical scheme of the application is an explosion device, and the application further comprises four parts of buffer devices, isolation devices and control devices.
The application comprises a core explosion device: mainly comprises a metal block, a belly body, a punch, explosive, an ignition device, a buffer device and a connecting device.
The second component is a buffer device, besides the buffer device of the explosion device, the buffer device is also needed, and the impulse of the explosion is smoothly conducted to the machine body, and the buffer device mainly comprises a mass block, a secondary spring, a backing plate and a main spring.
The third is an isolation device, an isolation system is needed, and when the explosion device is triggered by mistake, the safety of the helicopter can be ensured, and the high-strength material and the cylinder design are adopted.
The four-purpose control system and the protection device comprise a cockpit control button, an error protection box and a wire, and when the cockpit has an emergency, a pilot can directly trigger the ignition device.
The whole system is arranged under the whole cabin floor (the course corresponds to the main subtracting position), the frame beam is locally structurally reinforced, the buffer device is arranged, the isolation device is connected with the explosion device, and the whole device is connected with the structure.
The application provides an emergency buffer landing method and device for a helicopter, wherein a pilot is connected with an explosion device to detonate the explosion device before system faults or vortex rings and other emergency landings, and a large amount of energy can be generated due to the small weight of high-energy explosive, and reverse acting force acts on a main bearing structure of a helicopter body through the buffer device, so that the grounding speed of the helicopter can be slowed down, the small-speed grounding of the helicopter can be realized, and the use safety of the helicopter in emergency situations such as failure of a main propeller or a tail propeller or an engine is effectively improved.
The helicopter emergency buffer landing apparatus according to the present application will be described in further detail with reference to fig. 1-3.
The device comprises four parts of an explosion device, a buffer device, an isolation device and a control device.
The core explosion device comprises: 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 self buffer device of the explosion device, and the impulse of the explosion is smoothly conducted 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 guaranteed, high-strength materials are adopted, and the cylinder design is shown in fig. 3.
Control system and protection device including control button of cockpit, error protection box and wire, see fig. 3, pilot can trigger ignition device directly when cockpit is in emergency
And (3) carrying out local structural reinforcement on the frame beam under the whole cabin floor (the heading corresponds to the main subtracting position), installing a buffer device, and connecting the isolation device with the explosion device, wherein the whole device connecting structure is shown in figure 3.
Claims (6)
1. An emergency buffer landing device for a helicopter, comprising:
an explosive device disposed within the isolation device for generating a reverse acting impulse;
a buffer device disposed on the explosive device for buffering the reverse-acting impulse; wherein, under the ground plate of the helicopter cabin, the frame beam is locally structurally reinforced, and the buffer device is arranged;
an isolation device for preventing damage to the helicopter by the explosive device;
the control device is electrically connected with the explosion device and is used for controlling the explosion device;
wherein the explosive device comprises: the device comprises a metal block, a belly body, a punch, an explosive, an ignition device, a sub-buffer device and a connecting device;
the metal block is arranged in the abdomen body, a punch is arranged above the abdomen body, explosive is arranged above the punch and connected with the ignition device, the connecting device is arranged at the opening of the isolating device, the sub-buffering device is connected with the connecting device, and one end of the sub-buffering device is contacted with the ignition device.
2. The helicopter emergency buffer landing apparatus of claim 1, wherein the buffer apparatus comprises: the device comprises a main spring, a secondary spring, a backing plate and a mass block;
wherein the primary spring and the secondary spring are disposed between the backing plate and the mass.
3. The helicopter emergency buffer landing apparatus of claim 2, wherein the main spring is disposed in a middle portion of the pad, and the sub springs are symmetrically disposed at both sides of the main spring.
4. The helicopter emergency buffer landing apparatus of claim 1 wherein said isolation means is made of high strength isolated metal steel.
5. The helicopter emergency buffer landing apparatus of claim 1, wherein said control means comprises:
the cockpit control button is arranged in the error protection box;
the error protection box is used for protecting the control button of the cockpit from being triggered by errors; wherein, cockpit control button passes through the wire with explosion device connects.
6. The helicopter emergency buffer landing apparatus of 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 CN113928577A (en) | 2022-01-14 |
| CN113928577B true 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
| 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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| CN113928577A (en) | 2022-01-14 |
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