CN109522647A - A kind of helicopter crew's seat restraining system airworthiness compliance method - Google Patents
A kind of helicopter crew's seat restraining system airworthiness compliance method Download PDFInfo
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Abstract
This application discloses a kind of helicopter crew's seat restraining system airworthiness compliance methods, belong to aircraft authorization technical field.The method includes the steps one, determining constraint requirements relevant to helicopter member's seat；Step 2: parsing airworthiness requirement according to the constraint requirements；Step 3: proposing occupant-seat restraining system airworthiness compliance thinking；Step 4: proposing occupant-seat restraining system airworthiness compliance method.It has been obtained by this method a kind of for helicopter crew-seat restraining system airworthiness compliance universal method, seaworthiness clause is required and system airworthiness compliance method is combined together, it is complete for verifying work abundant, reduce the skill requirement of designer, airworthiness compliance risk is reduced, the evidence obtaining period of product is accelerated.
Description
Technical field
The application belongs to aircraft authorization technical field, and in particular to a kind of helicopter crew's seat restraining system accordance
Verification method.
Background technique
Seat is one of important component of helicopter, must install safety belt and shoulder belt to guarantee in defined flight shape
When state and emergency landing state inertial load effect, occupant is not damaged seriously.Seat is mainly by chair framework, chair
The part such as basin, height adjustment mechanism, front and back regulating mechanism, safety belt, seat cushions forms, and occupant-seat Major Systems include height
Spend regulating system, front and back regulating system, safety belt restraining system, design relation to the guarantor to helicopter pilot and occupant
Shield, the civilian airworthiness regulation in various countries and helicopter design specification all propose specific anti-pendant to seat, restraint system etc. and hit
It is required that the load-up condition born to occupant is also made that specific regulation.But currently without system comb out be applicable in it is straight
Machine occupant-seat restraining system airworthiness compliance method is risen, lacks the airworthiness compliance technological guidance to designer, it is difficult to protect
Card implements airworthiness requirement in helicopter crew-seat restraining system design.
Summary of the invention
At least one in order to solve the above-mentioned technical problem, the invention proposes a kind of helicopter crew's seat restraining system symbols
Conjunction property verification method, comprising:
Step 1: determining constraint requirements relevant to helicopter member's seat；
Step 2: parsing airworthiness requirement according to the constraint requirements；
Step 3: determining occupant-seat restraining system airworthiness compliance thinking；
Step 4: determining occupant-seat restraining system airworthiness compliance method.
Preferably, in step 3, the airworthiness compliance thinking includes:
The qualitative items damaged to occupant are determined to, determining all qualitative items are verified.
Preferably, in step 3, the airworthiness compliance thinking includes:
Pass through the bearing capacity of verification experimental verification seat.
Preferably, the bearing capacity includes:
Seat is able to bear limitation load without generating harmful permanent deformation；And
Armchair structure can be subjected to defined the limit dead load at least 3 seconds.
Preferably, the airworthiness compliance method of step 4 includes being tested by the way of analysis and calculating seat
Card.
Preferably, carrying out verifying to seat by the way of analysis and calculating includes:
The inertial load born using the loading coefficient computing system support of airworthiness regulation clause regulation or connection structure.
Preferably, the airworthiness compliance method of the step 4 includes being verified by laboratory test.
Helicopter crew proposed by the present invention-seat restraining system airworthiness compliance method, has obtained one by this method
Seaworthiness clause is required and system accordance helicopter crew-seat restraining system airworthiness compliance universal method by kind
Verification method is combined together, complete for verifying work sufficiently to reduce the skill requirement of designer, is reduced accordance and is tested
Risk is demonstrate,proved, the evidence obtaining period of product is accelerated.
Detailed description of the invention
Fig. 1 is the stream according to a preferred embodiment of helicopter crew's seat restraining system airworthiness compliance method of the present invention
Cheng Tu.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction with the application embodiment
In attached drawing, the technical solution in the application embodiment is further described in more detail.In the accompanying drawings, identical from beginning to end
Or similar label indicates same or similar element or element with the same or similar functions.Described embodiment is
A part of embodiment of the application, rather than whole embodiments.Embodiment below with reference to attached drawing description is to show
Example property, it is intended to for explaining the application, and should not be understood as the limitation to the application.Based on the embodiment in the application,
Every other embodiment obtained by those of ordinary skill in the art without making creative efforts belongs to this
Apply for the range of protection.Presently filed embodiment is described in detail with reference to the accompanying drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
The present invention provides a kind of helicopter crew's seat restraining system airworthiness compliance methods, as shown in Figure 1, comprising:
Step 1: determining constraint requirements relevant to helicopter member's seat；
Step 2: parsing airworthiness requirement according to the constraint requirements；
Step 3: determining occupant-seat restraining system airworthiness compliance thinking；
Step 4: determining occupant-seat restraining system airworthiness compliance method.
It is illustrated separately below.
S1, according to helicopter crew-seat restraining system design scheme, comb out occupant-seat restraining system correlation rule
Zhang Yaoqiu.
Occupant-seat restraining system is generally made of main framing, chair basin, safety belt, seat cushions etc., can be combed as example
Occupant/seat restraining system related regulatory requirements out, are related to main clause and basic demand is shown in Table 1.
The related regulatory requirements (few examples) that 1 occupant of table/seat restraining system is related to
S2, the related regulatory requirements combed out according to S1, parse airworthiness requirement.
Example is as follows: CCAR 29.561 " emergency landing situation-general provisions " and " the emergency landing dynamic feelings of CCAR 29.562
Condition " is to transport the more important seaworthiness clause of the suitable pendant property aspect of safety and structure in class aircraft cabin, to rotary wing aircraft occupant/about
Beam system has been withdrawn deposit requirement, and 29.561 lay particular emphasis on emergency landing dead load, it is desirable that helicopter structure design is able to bear clause rule
Load in fixed all directions, the static strength that these structures can be verified by slow test are met the requirements.And 29.562
Emergency landing dynamic loading is then laid particular emphasis on, new dynamic test requirements are increased to all seats in aircraft.
For passenger seat and its restraint system, 29.561,29.562 requirement is critically important.29.561 give
Basic security load level on seat and its restraint system all directions has investigated seat and its restraint system by slow test
Structural intergrity and permanent deformation under static load do not influence emergency evacuation；And the dynamic loading experiment that 29.562 clauses require is examined
Examined band dummy and consider under floor or seat limiting structure deformation truer dynamic load transmitting situation and personnel by
Condition of the injury condition, it is desirable that passenger seat and its restraint system without main load transfer path occur failure (restraint device do not turn off, seat
Do not depart from floor or its limiting structure), deformation be no more than that limitation, occupant is without major injuries.Further more, 29.562 for seat and its
The loading demands of restraint system forwardly and downwardly can be significantly larger than 29.561 requirement, but not have for the load in other directions
It requires, and the loading demands on these directions have in 29.561 clearly stipulate that seat and its restraint system also have to completely
Foot.
S3, occupant-seat restraining system airworthiness compliance thinking is proposed.
Example is as follows:
The general airworthiness compliance thinking of 29.561 clauses is as follows:
(1) passenger protection
29.561 require, and when emergency landing and (or) slight pendant collide water or land, occupant should be protected to avoid by regulation
Major injuries.This standard is pointed out to collide all reasonable chances that Lu Zhongying avoids major injuries to each occupant in slight pendant.This
Outside, it is necessary to protect an occupant from the injury of the qualitative items outside cabin interior and cockpit.For example, cockpit fire-suppression bottle must be by
This defined loading coefficient is constrained.If transmission device or engine arranged against occupant above occupant or after
Face must then be fixed by the loading coefficient of 29.561 (b) (3).For installation object, the conformational analysis of seat is carried out,
Most critical chair configuration is chosen by modes such as modeling, calculating and tests, carries out all directions as defined in 29.561 (b) (3)
Limit inertial load verification experimental verification.
The concrete thought of verification experimental verification: first by Strength co-mputation, choose suitable model to forward, downwards, upwards, to
Afterwards, the load for the passenger riding conditioning that laterally five kinds of situation analysis seats may occur, and above situation is screened,
Product configuration is analyzed, verification test is simplified.
The support reaction load of stress and seat in calculating process to each stress members of the seat screened.To seat
The strength check of main bearing member calculates the intensity of seat and aircraft connector and safety belt connector and seat connection.
Under normal circumstances, it needs to pass through verification experimental verification:
Seat is able to bear limitation load without generating harmful permanent deformation.Before the limitation load as defined in reaching, seat
Chair, which must not deform, influences its safe handling.After each state limit load test, testpieces does not generate harmful permanent deformation, seat
Chair deforms within the scope of defined magnitude, and the main bearing member of seat remains intact, and functions of seat is normal, and seat deforms not shadow
Ring its safe handling.
Armchair structure can be subjected to defined the limit dead load at least 3 seconds, and the main stressed member of seat should there is no separation
With fracture etc. breakoff phenomenons.
After applying and shedding ultimate load, seat meets defined permanent deformation limitation and requires, and does not influence making for seat
With function, occupant will not be caused to damage.
(2) retractable undercarriage
To the rotary wing aircraft equipped with retractable landing gear when 29.561 (b) of verifying are required, undercarriage should be at packing up
State, for which is rotary wing aircraft retractable for undercarriage.When landing on the ground more hardened, put down
Falling frame can be absorbed a large amount of landing shock energy, reduce the inertia that each qualitative items are born in occupant and aircraft and cabin
Load.In view of the emergency landing of rotary wing aircraft is likely to not use undercarriage, occupant and rotary wing aircraft structure institute
The inertial load of receiving is compared serious when being landed using undercarriage.In order to consider worst situation, 29.561 (b) (2) are wanted
The rotary wing aircraft that can be received for undercarriage is sought, to show to meet this requirement under undercarriage stowage state.
And 29.561 (d) require airframe structure must be designed to bear as defined in pendant hit load and protect fuel tank not
Rupture if there is retractable landing gear, is then all considered as the clause in two kinds of configurations not packing up in gear up and
The influence that undercarriage ruptures fuel system.
(3) each qualitative items that occupant may be injured in each occupant and cockpit should be according to the load of this regulatory requirement
Lotus situation is designed.
The verifying thinking of 29.562 clauses:
Although clear seat and restraint system must carry out dynamic impact test as required in 29.562 clauses, can basis
The aero seat structural strength of model verifies experience, corrected strength and settlement calculation model and method before, makes structure as far as possible
The calculated result of intensity can be close to truth, be to be fully ensured the success of later strength verification experimental verification.
When formulating aero seat strength modification experimental program, with reference to previous type and analysis report sufficiently should be calculated, closed
The formulation testing program of reason selects the constraint to tally with the actual situation and loading method and reasonably arranges test plan, can reduce
The time of structure verification and economic cost.
It, should be according to type before when carrying out dynamic test verifying to aero seat structure using CCAR29.562 (b) clause
Number aeronautic structure strength modification experience, design reasonable testing program, as far as possible in test simulation real load effect.
The corresponding verifying requirement of S4, comprehensive analysis occupant-seat restraining system typical case's clause, proposes occupant-seat constraint
System airworthiness compliance method.
Typical airworthiness compliance method is as follows:
S4.1 illustrative file: occupant-seat restraining system is typically designed requirement, the anti-flammability of material, function and sets
Standby installation and the requirement of label, label, are verified using illustrative file, illustrate the accordance of analytic process；
The file being related to has: " seat installation specification ", " seat design specification ", " seat installation instructions and limitation are wanted
Ask ", " seat maintenance handbook " etc..
S4.2 analysis/calculating: the support of loading coefficient computing system or connection structure institute for airworthiness regulation clause regulation
The inertial load of receiving；Using the experimental evidence and/or experience have shown that used analysis side that must have abundance when analysis method
Method is reliable or conservative.
Such as: for 29.561 clauses, rearwardly and upwardly load acts on seat load very little, can be by analyzing and counting
The method validation of calculation, acts on its Path of Force Transfer of the load of restraint system and force way is simple, can also be using analysis and meter
The method validation of calculation." being given and being demonstrate,proved through reasonable analysis according to the dynamic test result of similar model seat in 29.562 (b) moneys
It is bright." when verifying the strength and stiffness of seat and restraint system using analysis calculation method, it is necessary to there are similar seat and constraint
The dynamic test result form the basis of system.Small change is designed only for seat system herein to discuss, and does not consider installation factor.By
In seat system in actual use process, it may occur however that a series of change in design, to meet different customer requirements.Usually adopt
Change is checked with the method or similarity analysis that static models calculate, it is ensured that change meets initial design requirement.If
It counts small change and refers to that other characteristics of weight, balance, structural strength, reliability and operating characteristics or influence product seaworthiness are not significant
It influences.Such as seat-weight variation ± 3%, variation, forward direction chair backrest structure and the attachment of seat cushions in a certain range exist
A certain range of variation etc..It can be verified using analyses/calculation methods such as analysis, Strength co-mputations.It is related to file such as " seat
Chair installation strength calculates " etc..
S4.3 laboratory test: occupant-seat restraining system performance requirement, such as certain supports and connection structure,
When being difficult to show accordance using analysis method, can be verified by laboratory test.Test data obtained
It can be used for supporting the analysis of similar structure.
For example, be directed to 29.561 clauses, effect on the seat forward, it is laterally larger with down load, laboratory will be passed through
The method of test is verified；For 29.562 clauses, since impact test stress condition is complicated, cannot be calculated using simple
Analysis is verified, and is verified using laboratory test mode.Laboratory test related request is as follows:
(1) test platform: verifying CCAR29.562 clause can carry out on following four classes test platform:
Slowdown type tackle rigging: when rotary wing aircraft pendant is hit, impact is the generation in the form of deceleration, therefore to slow down
The equipment that degree form generates shock pulse, the load applied in test are more true to nature.The test platform is in order to be required
Test shock pulse corresponding to enough speed, to have a test acceleration stage, if but boost phase it is too big, it will
Cause testpieces or dummy's initial position to move forward, influences test result.
Accelerating type tackle rigging: acceleration tackle rigging usually uses high pressure gas (HYGE) accelerator of hydraulic control,
It can provide an acceleration controlled impact test pulse in on-test, and dummy and test specimen are by the opposite of velocity vector
(with contrary used by deceleration test) is installed in direction, and to compensate the variation of impact direction, at this moment there will be no impacts
The problem of dummy caused by preacceleration or test specimen leave home position, because coaster does not move before shock pulse generates.
Since deceleration rail length is limited, cause deceleration relatively high and meanwhile may immediately assault phase, but the dynamic tested is rung
It should also follow closely in assault phase, influence dynamic response, it is also possible to change test result.
Collision-rebound tackle rigging: hydraulic test is " collision-rebound " tackle rigging.In such a device, work as movement
Coaster contact braking system when collide, braking system stores the energy of collision, and energy is then returned to coaster, makes
It springs back in the opposite direction.The advantages of this equipment, is that it only needs to generate the half for colliding required speed (assuming that effect
100%) rate is.Therefore, which can be than slowdown type or the guide rail much shorter of accelerating type equipment.Disadvantage then integrates
The problems of slowdown type and accelerating type tackle rigging.
Fall tower: vertical test facility includes falling tower (deceleration) and two kinds of vertical accelerator, and falling tower facility is to be easiest to build
One of the equipment made and run, is commonly used.Coaster is accelerated to reach impact velocity with centrifugal force in such a device, therefore
Complicated mechanical acceleration system is not needed.
(2) test equipment: dynamic test process is related to two class of electrical measurement and flash ranging instrument.
(3) testpieces: at least 2, installation verifying needs to make a concrete analysis of.
(4) it tests mounting rack: determining the need for simulation floor deformation by test requirements document.
(5) test prepares: restraint system, seat and various instruments including positioning and fixing emulate dummy, dummy.All
To prepare according to " the most precarious position " of set test determination.And seat system deformation test position mark, to test
The deformation of journey test equipment capture seat certain point.
(6) determine test result.
For example seat deforms again: due to the peptizaiton of the energy absorber of seat design in test, or due to seat knot
The plastic deformation of component may cause seat deformation.If deformed excessive, it is possible to interfere occupant's emergency escape.Each model
The design of seat may all have any different in this regard, therefore should be assessed according to their own deformation characteristic.If ground
Plate deformation is applicable in, then the consistency measured after test should being kept preceding and test.If test before measurement be floor deformation it
Preceding progress, then the measurement after testing should carry out after eliminating floor deformation, if instead the measurement before test is become on floor
It is carried out after shape, then the measurement after testing should carry out before eliminating floor deformation.
1) forward or backward: the deformation maximum forward or backward that seat is presented must not exceed 3 inches (75mm).In this way,
The distance between undeformed two rows seat minimum should be 9 inches (228mm) or 6 inches (150mm) add practical forward/backward
Deflection.
2) downwards: there is no limit as long as the foot or leg of passenger are not limited permanent deformation by deformation downwards.
3) seat reverses: seat bottom torsion permanent deformation should not result in: be more than 20 degree of downward pitch angle from horizontal plane
Or the upward pitch angle more than 35 degree.Torsional deflection, center line of the chair basin in seat bottom are measured between the forward and backward end of chair basin
On.Chair basin torsion in any case should not block passenger.
4) lateral: the seat of deformation should not occupy the vertical passage space of requirement, 25 inches (635mm) high more than floor
In the range of, it must not exceed 1.5 inches (38mm).So should determine what height various parts of seat is at before the test.Ground
More than plate 25 inches (635mm) or higher vertical passage space do not allow Changeable shape chair to occupy more than 2.0 (50mm) inches.
Test data is judged: the dynamic test that seat system carries out should meet to be sentenced cited by CCAR25.562 (c) clause
According to.
When being verified using dynamic test, some requirements in horizontal impact test and vertical impact test are as follows:
(1) impact test apparatus, two kinds of tests can be completed on same set of experimental rig.
(2) anthropomorphic test dummies, the simulation people installed in test, should be able to simulate the bending of the neck and waist of people, chest
Portion can sink, and the joints such as arm, elbow and knee can be move freely, and its frictional force is adjustable.The quality for simulating people is 77 kilograms,
In normal sitting position and the safe dress such as fasten corresponding waistband, shoulder belt.
(3) seat is installed, and when vertical impact is tested, seat is swung back 60 ° and is fixed on slide unit, opposite to simulate aircraft longitudinal axis
Level tilts upwardly 60 ° of posture.When horizontal impact is tested, the installation of seat is along direction of motion left avertence or 10 ° of right avertence, one group
The installation guide rail of seat is parallel with slide unit, and another group is lifted in front end and make it with slide unit plane at 10 ° of angles and simultaneously along the longitudinal axis
10 ° of rotation, to simulate influence of the engine room floor deformation to seat and connection in emergency landing.
In impact test, the test data of various needs should be acquired, and is analysis test knot by video recording, high-speed photography etc.
Fruit provides necessary data.Data collected should all meet the index of clause proposition.
Head injury criterion HIC value can be calculated as follows:
When calculating, the selection of time interval is critically important, and clause requires to be no more than 0.05 second, selects too small to make calculation amount
It is too big, and select greatly the spike of a (t) can then artificially evened up very much, so as to cause the incorrect of result.It is risen by difference
Time beginning can get a series of calculated value, therefrom selects the maximum as HIC value, recognizes if HIC is less than or equal to 1000
To meet the requirements.
Dynamic impact test example is as follows:
Pilot set and passenger seat are using the 50th percentile standard dummy counterweight to 77kg and by the 29.562nd article
Emergency landing dynamic condition carries out dynamic impact test, and testing equipment uses horizontal impact testing stand, and test basic demand is shown in Table
2。
Table 2 tests basic demand
The report of seat seaworthiness airworthiness compliance should be provided after the completion of test, provide analysis conclusion.
S4.4 equipment qualification: for integral device, the component etc. of buying, applicant identifies to equipment, component
During, by analysis, experiments have shown that these outsourcing devices and its corresponding support construction meet airworthiness requirement.
Such as safety belt meets the requirement of CTSO-C114, and obtains corresponding seaworthiness certificate, provides equipment symbol by supplier
Conjunction property statement, technical standard order project approval book menu (CTSOA) etc., it was demonstrated that equipment qualification.
S5, in summary, forms general occupant-seat restraining system airworthiness compliance Methods Instruction.
The present invention provides a kind of helicopter crew-seat restraining system airworthiness compliance method based on seaworthiness authorization, leads to
Cross this method obtained it is a kind of for helicopter crew-seat restraining system airworthiness compliance universal method, by seaworthiness clause
It is required that be combined together with system airworthiness compliance method, it is complete for verifying work abundant, reduce the experience of designer
It is required that reducing airworthiness compliance risk, the evidence obtaining period of product is accelerated.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (7)
1. a kind of helicopter crew's seat restraining system airworthiness compliance method characterized by comprising
Step 1: determining constraint requirements relevant to helicopter member's seat；
Step 2: parsing airworthiness requirement according to the constraint requirements；
Step 3: determining occupant-seat restraining system airworthiness compliance thinking；
Step 4: determining occupant-seat restraining system airworthiness compliance method.
2. helicopter crew's seat restraining system airworthiness compliance method according to claim 1, which is characterized in that step
In three, the airworthiness compliance thinking includes:
The qualitative items damaged to occupant are determined to, determining all qualitative items are verified.
3. helicopter crew's seat restraining system airworthiness compliance method according to claim 2, which is characterized in that step
In three, the airworthiness compliance thinking includes:
Pass through the bearing capacity of verification experimental verification seat.
4. helicopter crew's seat restraining system airworthiness compliance method according to claim 3, which is characterized in that described
Bearing capacity includes:
Seat is able to bear limitation load without generating harmful permanent deformation；And
Armchair structure can be subjected to defined the limit dead load at least 3 seconds.
5. helicopter crew's seat restraining system airworthiness compliance method according to claim 3, which is characterized in that step
Four airworthiness compliance method includes being verified by the way of analysis and calculating to seat.
6. helicopter crew's seat restraining system airworthiness compliance method according to claim 5, which is characterized in that use
Analysis and the mode calculated carry out verifying to seat and include:
The inertial load born using the loading coefficient computing system support of airworthiness regulation clause regulation or connection structure.
7. helicopter crew's seat restraining system airworthiness compliance method according to claim 1, which is characterized in that described
The airworthiness compliance method of step 4 includes being verified by laboratory test.
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| CN111222268A (en) * | 2019-12-04 | 2020-06-02 | 中国直升机设计研究所 | Helicopter short-wing overwater forced landing strength calculation method provided with emergency floating system |
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| CN113343370B (en) * | 2020-12-29 | 2024-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Plastic strain control method for simulation analysis of impact test of aviation seat |
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