CN108844730A - Test the testing stand of fighter-pilot's ejection escape neck protective device safety - Google Patents
Test the testing stand of fighter-pilot's ejection escape neck protective device safety Download PDFInfo
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- CN108844730A CN108844730A CN201810691129.XA CN201810691129A CN108844730A CN 108844730 A CN108844730 A CN 108844730A CN 201810691129 A CN201810691129 A CN 201810691129A CN 108844730 A CN108844730 A CN 108844730A
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- Prior art keywords
- protective device
- dummy
- neck
- pilot
- fighter
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
Abstract
A kind of testing stand for testing the protective device safety of fighter-pilot's ejection escape neck, including firm banking, firm banking is connected with cylinder, the piston rod of cylinder is connect with dummy's incidence fixed plate, dummy incidence fixed plate side is connected with protective device mounting plate, and protective device mounting plate is connected on sliding rail guide sleeve, and sliding rail guide sleeve is placed on guide rod, guide rod bottom end connects on the fixed base, and guide rod top is equipped with the postive stop baffle of sliding rail guide sleeve；Dummy's incidence fixed plate is connected with dummy neck lower end, and the first 3-axis acceleration sensor is installed in the manikin head of dummy neck upper end connection, and manikin head wears aircrew helmet；It is connected with protective device on protective device mounting plate, the second 3-axis acceleration sensor is fixed on protective device；The present invention is pushed using cylinder enemy neck, promotion of the simulated rocket to human body on ejector seat, and be capable of measuring incidence is influenced by external force simultaneously from high acceleration of experiencing, and is had the advantages that at low cost.
Description
Technical field
The present invention relates to ejection life saving equipment the field of test technology, and in particular to a kind of test fighter-pilot ejection is rescued
The testing stand of raw neck protective device safety.
Background technique
When fighter-pilot's ejection escape incidence be weak link, incidence by acceleration and windblast etc. because
Element influences that whipping can occur, thus lethal or cause injury.Head will receive downward high acceleration in ejection and move downward, existing
Protective device is moved downward in ejection with head, and specific position is fixed on head, is prevented from getting rid of and be beaten.But protective device moves
When whether can apply biggish power to head and still need to verify so as to cause incidence damage, existing verification mode uses rocket projectile
Seat test is penetrated, site requirements is spacious, and impacted factor is more, and cost is high.
Chinese patent CN204286738U and United States Patent (USP) US4161874 successively reports two kinds of measurement incidence stress
System；Wherein the specific technical solution of Chinese patent CN204286738U is that incidence model is fixed on sliding rail, and inside adds
Force snesor is filled, movement and stress when analogue head is struck by bullet；The specific technical solution of United States Patent (USP) US4161874 is
Incidence model is fixed on test board, test board all directions place force snesor and acceleration transducer, test neck
Force-bearing situation when portion is struck.
But Chinese patent CN204286738U and United States Patent (USP) US4161874 have a common technical disadvantages：It can not
Measurement incidence itself is influenced by external force simultaneously by high acceleration, and can only passively test is influenced by external force.
Summary of the invention
In order to overcome the disadvantages of the above prior art, the object of the present invention is to provide a kind of test fighter-pilots
The testing stand of ejection escape neck protective device safety is capable of measuring incidence from high acceleration of experiencing simultaneously by external force
It influences, has the advantages that at low cost.
To achieve the goals above, the present invention uses following technical scheme：
A kind of testing stand for testing the protective device safety of fighter-pilot's ejection escape neck, including firm banking 1,
Firm banking 1 is connected with cylinder 2, and the piston rod of cylinder 2 is connect with dummy's incidence fixed plate 3,3 side of dummy's incidence fixed plate
Face and protective device mounting plate 10 connect, and protective device mounting plate 10 is connected on sliding rail guide sleeve 9, and sliding rail guide sleeve 9 is placed on guide rod 8
On, 8 bottom end of guide rod is connected on firm banking 1, and 8 top of guide rod is equipped with the postive stop baffle 11 of sliding rail guide sleeve 9；
Dummy's incidence fixed plate 3 is connected with 4 lower end of dummy neck, peace in the manikin head 5 of 4 upper end of dummy neck connection
The first 3-axis acceleration sensor 7 is filled, manikin head 5 wears aircrew helmet 6；
It is connected with protective device 12 on the protective device mounting plate 10, the two or three axis is fixed on protective device 12 and is added
Velocity sensor 13, protective device 12 are affixed with aircrew helmet 6 at the beginning or do not contact.
1.5 meters of the piston rod movement of the cylinder 2 is longer.
The cylinder 2 is replaced using hydraulic cylinder or spring cylinder.
The dummy neck 4 is replaced using damping system, or is replaced using spring.
First 3-axis acceleration sensor 7 is replaced using force snesor, or use can derive stress
Sensor be replaced.
The sliding rail guide sleeve 9 and guide rod 8 are replaced using the connection type of attachment of sliding rail.
The manikin head 5 and dummy neck 4 is chosen using pilot's neck ministerial standard.
The present invention has the following advantages that due to taking above technical scheme：
1, the present invention using cylinder as power device, to the promotion simulated rocket of incidence to human body on ejector seat
It pushes, higher acceleration can be provided to incidence model, also avoided using ejector seat, to greatly reduce
Experimentation cost.
2, the present invention repeated multiple times can utilize, to effectively control cost, and meet environmentally protective requirement.
3, use of the invention is built simple without spacious space.
4, the present invention can carry out the test of a variety of different postures of incidence.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the present invention without installation protective device.
Fig. 2 is that the present invention installs the schematic diagram after protective device additional.
Fig. 3 is that the present invention installs the axis side view after protective device additional.
Fig. 4 is the schematic diagram after the completion of cylinder action of the present invention.
Fig. 5 is the schematic diagram of incidence lateroflexion of the present invention position.
Fig. 6 is the schematic diagram of incidence torsiversion of the present invention.
Fig. 7 is the schematic diagram of incidence of the present invention while lateroflexion and torsiversion.
Specific embodiment
The present invention will be described in detail with reference to the accompanying drawing.
Referring to Fig.1, a kind of testing stand for testing the protective device safety of fighter-pilot's ejection escape neck, including it is solid
Determine pedestal 1, cylinder 2 has been bolted in firm banking 1, and the piston rod of cylinder 2 passes through bolt and dummy's incidence fixed plate 3
Connection, 3 side of dummy's incidence fixed plate and protective device mounting plate 10 connect, and protective device mounting plate 10 is connected to sliding rail and leads
On set 9, sliding rail guide sleeve 9 is placed on guide rod 8, and 8 bottom end of guide rod is connected on firm banking 1, and 8 top of guide rod is equipped with sliding rail guide sleeve 9
Postive stop baffle 11；
By being connected by bolt or other modes with 4 lower end of dummy neck in dummy's incidence fixed plate 3, dummy's neck
First 3-axis acceleration sensor 7 is installed, manikin head 5 wears aircrew helmet 6 in the manikin head 5 of 4 upper end of portion connection；
As shown in Figures 2 and 3, protective device 12, and protective device 12 are connected on the protective device mounting plate 10
On be fixed with the second 3-axis acceleration sensor 13, protective device 12 is affixed with aircrew helmet 6 at the beginning or does not contact.
1.5 meters of the piston rod movement of the cylinder 2 is longer, and pilot is added on head in very short catapulting distance
Speed effect can bow completely, and piston rod movement distance can be met the requirements.
The operation principle of the present invention is that：
When not starting to work, the piston rod of cylinder 2 is in initial position, as shown in Figure 2；When start-up operation, the work of cylinder 2
Stopper rod pushes dummy's incidence fixed plate 3 quickly to move, and dummy's incidence fixed plate 3 is moved upwards along guide rod 8；Due to by
The effect of the downward acceleration in direction, manikin head 5 can turn forward；Start with cylinder 2, protective device 12 is unfolded, with flight
Member's helmet 6 contacts with each other and envelope aircrew helmet 6, moves downward with head or pressing head, finally consolidates manikin head 5
Due to final position, to avoid incidence whipping from playing protective action, as shown in Figure 4；Postive stop baffle 11 can limit sliding rail
Guide sleeve 9 is detached from guide rod 8, in case sliding rail guide sleeve 9 flies out and causes danger.
To measure in above process, power and incidence institute of the protective device 12 to dummy neck 4 and the application of manikin head 5
Whether the high acceleration superposition received causes incidence to damage, and the present invention is using the first 3-axis acceleration sensor 7 come measuring head
Neck stress can measure the acceleration in three directions suffered by manikin head 5 by the first 3-axis acceleration sensor 7, change
It is counted as the form of power, so as to judge whether incidence is damaged.It can be surveyed by the second 3-axis acceleration sensor 13
Calculate three directional accelerations that process is unfolded in protective device 12, with manikin head 5 suffered by compared with acceleration, can probe into anti-
The influence that the expansion acceleration of protection unit 12 damages incidence, so that the improvement to protective device 12 provides modification.
The test that the present invention is in neutral position (as shown in Figure 1) in addition to that can carry out incidence, by adjusting headform
Neck posture can also carry out the test in unfavorable position.As shown in figure 5, dummy's incidence is in lateroflexion position；Such as figure
Shown in 6, dummy's incidence is in torsiversion；As shown in fig. 7, not only lateroflexion but also the torsion of dummy's incidence.By to 4 kinds of incidences
The corresponding damage of different postures is analyzed, and optimal ejection posture can be compared, and can analyze different postures for damage
The influence of wound.
The various embodiments described above are merely to illustrate the present invention, wherein the structure of each component, connection type etc. are all can be
Variation, all equivalents and improvement carried out based on the technical solution of the present invention should not be excluded of the invention
Except protection scope.
Claims (7)
1. a kind of testing stand for testing the protective device safety of fighter-pilot's ejection escape neck, including firm banking (1),
It is characterized in that：Firm banking (1) is connected with cylinder (2), and the piston rod of cylinder (2) is connect with dummy's incidence fixed plate (3),
Dummy's incidence fixed plate (3) side and protective device mounting plate (10) connection, protective device mounting plate (10) are connected to sliding rail
On guide sleeve (9), sliding rail guide sleeve (9) is placed on guide rod (8), and guide rod (8) bottom end is connected on firm banking (1), guide rod (8) top
Postive stop baffle (11) equipped with sliding rail guide sleeve (9)；
Dummy's incidence fixed plate (3) is connected with dummy neck (4) lower end, the manikin head (5) of dummy neck (4) upper end connection
The first 3-axis acceleration sensor of interior installation (7), manikin head (5) wear aircrew helmet (6)；
It is connected with protective device (12) on the protective device mounting plate (10), protective device is fixed with the two or three axis on (12)
Acceleration transducer (13), protective device (12) are affixed with aircrew helmet (6) at the beginning or do not contact.
2. a kind of test for testing the protective device safety of fighter-pilot's ejection escape neck according to claim 1
Platform, it is characterised in that：1.5 meters of the piston rod movement or longer of the cylinder (2).
3. a kind of test for testing the protective device safety of fighter-pilot's ejection escape neck according to claim 1
Platform, it is characterised in that：The cylinder (2) is replaced using hydraulic cylinder or spring cylinder.
4. a kind of test for testing the protective device safety of fighter-pilot's ejection escape neck according to claim 1
Platform, it is characterised in that：The dummy neck (4) is replaced using damping system, or is replaced using spring.
5. a kind of test for testing the protective device safety of fighter-pilot's ejection escape neck according to claim 1
Platform, it is characterised in that：First 3-axis acceleration sensor (7) is replaced using force snesor, or use can push away
The sensor of export stress is replaced.
6. a kind of test for testing the protective device safety of fighter-pilot's ejection escape neck according to claim 1
Platform, it is characterised in that：The sliding rail guide sleeve (9) and guide rod (8) is replaced using the connection type of attachment of sliding rail.
7. a kind of test for testing the protective device safety of fighter-pilot's ejection escape neck according to claim 1
Platform, it is characterised in that：The manikin head (5) and dummy neck (4) is chosen using pilot's neck ministerial standard.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810691129.XA CN108844730A (en) | 2018-06-28 | 2018-06-28 | Test the testing stand of fighter-pilot's ejection escape neck protective device safety |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810691129.XA CN108844730A (en) | 2018-06-28 | 2018-06-28 | Test the testing stand of fighter-pilot's ejection escape neck protective device safety |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108844730A true CN108844730A (en) | 2018-11-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810691129.XA Pending CN108844730A (en) | 2018-06-28 | 2018-06-28 | Test the testing stand of fighter-pilot's ejection escape neck protective device safety |
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| CN (1) | CN108844730A (en) |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2467764A (en) * | 1946-02-18 | 1949-04-19 | Martin James | Apparatus for testing on the ground ejection seats intended for use in aircraft |
| US4004763A (en) * | 1974-07-15 | 1977-01-25 | Lockheed Aircraft Corporation | Articulated high "G" pilot S seat |
| US4395001A (en) * | 1978-03-27 | 1983-07-26 | The United States Of America As Represented By The Secretary Of The Navy | Attitude selective aircrew escape control |
| US4813634A (en) * | 1985-01-05 | 1989-03-21 | Zuck Daniel R | Flying emergency ejection seat |
| US5039035A (en) * | 1989-05-03 | 1991-08-13 | Smiths Industries Public Limited Company | Helmet assembly with inflatable actuators |
| JPH092397A (en) * | 1995-06-23 | 1997-01-07 | Shimadzu Corp | Ejector seat |
| CN201465338U (en) * | 2009-06-26 | 2010-05-12 | 北京欣远诚业科技有限公司 | Ejection training simulator |
| US7819031B2 (en) * | 2008-03-27 | 2010-10-26 | The United States Of America As Represented By The Secretary Of The Navy | Parachute opening and shock emulator |
| CN202838722U (en) * | 2012-09-26 | 2013-03-27 | 中国人民解放军空军军训器材研究所 | Airplane ejection lifesaving seat simulating device |
| CN204286738U (en) * | 2014-12-18 | 2015-04-22 | 公安部第一研究所 | The damage measure device of incidence when a kind of bulletproof halmet is hit |
| CN105068448A (en) * | 2015-08-19 | 2015-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Semi-physical simulation method of integrated life support system |
| CN107806976A (en) * | 2017-11-13 | 2018-03-16 | 南京理工大学 | The damage measure device of incidence when a kind of bulletproof halmet is hit |
| CN107817084A (en) * | 2017-09-15 | 2018-03-20 | 中国飞行试验研究院 | A kind of extraordinary pilots head Gx is to overload prediction method |
-
2018
- 2018-06-28 CN CN201810691129.XA patent/CN108844730A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2467764A (en) * | 1946-02-18 | 1949-04-19 | Martin James | Apparatus for testing on the ground ejection seats intended for use in aircraft |
| US4004763A (en) * | 1974-07-15 | 1977-01-25 | Lockheed Aircraft Corporation | Articulated high "G" pilot S seat |
| US4395001A (en) * | 1978-03-27 | 1983-07-26 | The United States Of America As Represented By The Secretary Of The Navy | Attitude selective aircrew escape control |
| US4813634A (en) * | 1985-01-05 | 1989-03-21 | Zuck Daniel R | Flying emergency ejection seat |
| US5039035A (en) * | 1989-05-03 | 1991-08-13 | Smiths Industries Public Limited Company | Helmet assembly with inflatable actuators |
| JPH092397A (en) * | 1995-06-23 | 1997-01-07 | Shimadzu Corp | Ejector seat |
| US7819031B2 (en) * | 2008-03-27 | 2010-10-26 | The United States Of America As Represented By The Secretary Of The Navy | Parachute opening and shock emulator |
| CN201465338U (en) * | 2009-06-26 | 2010-05-12 | 北京欣远诚业科技有限公司 | Ejection training simulator |
| CN202838722U (en) * | 2012-09-26 | 2013-03-27 | 中国人民解放军空军军训器材研究所 | Airplane ejection lifesaving seat simulating device |
| CN204286738U (en) * | 2014-12-18 | 2015-04-22 | 公安部第一研究所 | The damage measure device of incidence when a kind of bulletproof halmet is hit |
| CN105068448A (en) * | 2015-08-19 | 2015-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Semi-physical simulation method of integrated life support system |
| CN107817084A (en) * | 2017-09-15 | 2018-03-20 | 中国飞行试验研究院 | A kind of extraordinary pilots head Gx is to overload prediction method |
| CN107806976A (en) * | 2017-11-13 | 2018-03-16 | 南京理工大学 | The damage measure device of incidence when a kind of bulletproof halmet is hit |
Non-Patent Citations (1)
| Title |
|---|
| 吴明磊等: ""弹射时装显示头盔对人体的生物力学效应"", 《中华航空航天医学杂志》 * |
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Application publication date: 20181120 |
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