CN108664685A - A kind of unmanned helicopter fuselage interior structural optimization method - Google Patents
A kind of unmanned helicopter fuselage interior structural optimization method Download PDFInfo
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- CN108664685A CN108664685A CN201810223117.4A CN201810223117A CN108664685A CN 108664685 A CN108664685 A CN 108664685A CN 201810223117 A CN201810223117 A CN 201810223117A CN 108664685 A CN108664685 A CN 108664685A
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- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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Abstract
The present invention relates to a kind of unmanned helicopter fuselage interior structural optimization methods：Step 1: establishing the finite element model of fuselage interior structure；Step 2: determining outer carry；Step 3: choosing Optimal Parameters；Step 4: carrying out structure optimization calculating.The present invention carries out real structure using curved surface and wire frame to simplify modeling, is simulated in order to apply mechanically beam in finite element and plate mould component；Boundary condition is applied using clamped connection and hinged connection respectively, remains the inherent characteristic of all connection types in structure connection；Gravity and the additional force of overload are all reduced to overload additional force, simplify the applying mode of outer load；The thickness parameter as an optimization for choosing beam element, does not change the shape of main body frame；It uses experience and optimizes the mode combined with algorithm optimization, accelerate the calculating speed of optimization method.To sum up, the present invention is a kind of efficient, general unmanned helicopter fuselage interior structural optimization method.
Description
Technical field
The present invention relates to aviation Astronautics technical fields, it is proposed that a kind of unmanned helicopter fuselage interior structure optimization side
Method.
Background technology
Unmanned helicopter refer to flown by radio ground remote control or autonomous control flight can VTOL rotation
Wing power not manned vehicle, it have take off vertically, hovering and the features such as flight all around.Unmanned helicopter
High maneuverability and light concealment make countries in the world be classified as an important content of military developments, in military battlefield
Purposes is very extensive, include mainly military surveillance and with the aspect of military communication two；At civilian aspect, be mainly used in exploration,
Take photo by plane, line walking, fire extinguishing disaster relief etc..
The main space of manned helicopter fuselage interior is the cockpit of driver and occupant, needs to be equipped with seat, floor, cabin
The facilities such as door, windshield are to provide more comfortable riding space and the good visual field；And unmanned helicopter without the concern for
These are the facility of driver and passenger's service, and the fuselage interior structure of unmanned helicopter is compacter, and main composition part is to realize
The mounting bracket of Aerial Electronic Equipment and Aerial Electronic Equipment needed for unmanned flight.The fuselage design of unmanned helicopter can be divided into outside fuselage
Shape designs and fuselage interior structure design.Do not have to consider driver and passenger to the visual field in the fuselage appearance design of unmanned helicopter
It is required that fuselage design is more slender can to effectively reduce air drag；Fuselage interior structure design mainly considers Aerial Electronic Equipment
Installation and maintenance, while there is enough intensity and reliability.Both configuration design and fuselage interior structure design influence each other,
Iteration progress is generally required in the design.
Unmanned helicopter fuselage interior structure optimization is a follow-up work of fuselage interior structure design, is not changing machine
By optimizing the layout and size of fuselage interior structure on the basis of body internal structure general frame, realize strong needed for meeting
Make fuselage interior structure total weight minimum on the basis of degree and reliability, to realize the purpose for mitigating weight.Preliminary design
Fuselage interior structure often not only cannot be satisfied intensity, reliability, but also have certain optimization space in terms of weight.Fuselage interior
Structure optimization exactly finds a tradeoff between weight and intensity, reliability, is obtained with the construction weight of minimum required strong
Degree and reliability.
The present invention proposes a kind of unmanned helicopter fuselage interior structural optimization method, and giving can grasp in engineering conscientiously
The realization step of work is used for the optimization of unmanned helicopter fuselage interior structure design, on the basis of meeting intensity and reliability
Realize minimum construction weight.
Invention content
<1>Goal of the invention
Present invention aims at a kind of unmanned helicopter fuselage interior structural optimization method is proposed, maintaining outside initial fuselage
On the basis of shape and fuselage interior structure design, required intensity and reliability are realized with minimum construction weight.
<2>Technical solution
To achieve the goals above, the technical solution adopted by the present invention is that：First, with curved surface and wire frame to unmanned helicopter
Fuselage interior structure carries out simplifying modeling, replaces the sheet material portions such as frame, panel with curved surface, steelframe and rib etc. are replaced with wire frame
Proximate matter part is simulated curved surface, is simulated wire frame with beam in corresponding finite element model with plate shell, and according in practical structures
The boundary condition of clamped connection and hinged connection Bu Tong applied respectively in finite element model；Secondly, up and down all around 6 are determined
Source of the overload factor in a direction as outer load, takes the centroid position of each Aerial Electronic Equipment as load(ing) point；Then, beam is chosen
The thickness in unit section parameter as an optimization allows section with structural stress index as an optimization meeting in certain range of stress
Thickness minimum is so that construction weight is most light；Last optimization process is combined using experience optimization with optimization algorithm global optimizing
Method optimize, experience optimization by designer design initial stage by way of manually calculating, rule of thumb adjustment tie
Thickness in structure obtains the effect that intensity mitigates overall weight that improves, and algorithm optimization utilizes numerical method using optimizing algorithm
It is solved.The overall flow figure of the present invention is shown in attached drawing 1.
The present invention proposes a kind of unmanned helicopter fuselage interior structural optimization method, specifically comprises the following steps：
Step 1: establishing the finite element model of fuselage interior structure
The entirety of the mounting means and mounting structure of Aerial Electronic Equipment is had determined that in the design phase of fuselage interior structure
Frame, the Optimization Work that the present invention designs are carried out mainly for the size of mounting structure.Nobody is gone straight up to curved surface and wire frame
Machine fuselage interior structure carries out simplifying modeling, replaces the sheet material portions such as frame, panel with curved surface, steelframe and rib are replaced with wire frame
Equal proximate matters part, is simulated curved surface, is simulated wire frame with beam in corresponding finite element model with plate shell.Due to fuselage interior knot
Structure is connected in fuselage main body structure, and connection type can be divided into clamped connection and hinged two kinds of connection, in above-mentioned finite element
It needs to apply the boundary condition in finite element model respectively according to the connection type in practical structures in model.
Step 2: determining outer carry
The overload production that the stress of unmanned helicopter internal structure is brought essentially from the gravity and flare maneuver of Aerial Electronic Equipment
Raw additional force, since the additional force overload that can be used uniformly all related with Aerial Electronic Equipment quality of gravity and overload generation carrys out table
Show, needs to consider respectively up and down the overload in 6 directions all around.Take the centroid position of each Aerial Electronic Equipment as load(ing) point,
It can determine the size of power and torque in outer carry completely using overload factor, each equipment quality, equipment centroid position.Its
In, the product of overload factor and equipment quality is exactly the stress size of equipment, Impact direction along overload direction；According to step
Equipment stress, is transmitted in fuselage interior structure to be optimized by one connection relation determined according to the transfer principle of power, generates
The effect of power and torque.
Step 3: choosing Optimal Parameters
In order to be optimized to system structure, to reduce stress raisers and total quality, chooses beam element and cut
The thickness in face parameter as an optimization, with structural stress index as an optimization, meet allowed in certain range of stress section thickness most
It is small so that construction weight is most light.To same structure, under same outer carry, the smaller internal stress of section thickness is bigger,
Stress excessive component needed to increase thickness reduce stress, for the component of understressing should reduce thickness mitigate
Construction weight, final realize need to use construction weight minimum under stress index.
Step 4: carrying out structure optimization calculating
Use experience optimization is optimized with optimization algorithm global optimizing combined method.
Experience optimization is carried out first.Analysis and summary is carried out to the stress state under different overload situations, it is rule of thumb right
The wherein larger position of stress suitably increases thickness, for the appropriate reduced thickness in stress smaller part position, re-starts calculating, obtains new
Model weight and stress state, if model weight mitigates and model maximum stress is less than allowable value, iteration success is being repaiied
Change and continues iteration optimization on the basis of rear model；Otherwise iteration fails, then continues iteration optimization, this mode on the basis of master mould
Suitable for designing initial stage, construction weight is quickly reduced based on designer's experience.Detailed process is as shown in Fig. 2.
Then algorithm global optimizing is optimized.There is coupling in the influence due to each Optimal Parameters to structural stress state
Effect, adjustment thickness parameter may cause to find less than meeting the combination parameter of material allowable value, thus use instead optimization algorithm into
Row global optimizing.Under this approach, total lightest for optimization aim with structure by giving each parameter value range, it uses
The parametric modeling method fast and automatically modeling of finite element software simultaneously solves, and result is fed back to optimization algorithm end, by calculating
Method selects suitable combination parameter to be iterated optimizing.Detailed process is as shown in Fig. 3.Common optimization algorithm has gradient decline
The heuristic values such as the traditional algorithms such as method, Newton method and simulated annealing, genetic algorithm.The usual base of traditional algorithm
The relationship between variables and objective function, it is close to optimal solution by way of Step wise approximation；And heuritic approach does not need
The relationship between variables and objective function is solved, thus there is better applicability, is usually also required to more iterations.
<3>Advantage effect
A kind of unmanned helicopter fuselage interior structural optimization method of the present invention, carries out real structure using curved surface and wire frame
Simplify modeling, is simulated in order to apply mechanically beam in finite element and plate mould component；Using clamped connection and hinged connection point
Do not apply boundary condition, remains the inherent characteristic of all connection types in structure connection；By the additional force of gravity and overload
It is all reduced to overload additional force, simplifies the applying mode of outer load；The thickness parameter as an optimization for choosing beam element, does not change master
The shape of body frame；It uses experience and optimizes the mode combined with algorithm optimization, accelerate the calculating speed of optimization method.It is comprehensive
On, the present invention is a kind of efficient, general unmanned helicopter fuselage interior structural optimization method.
Description of the drawings
Fig. 1 is overall flow figure of the present invention.
Fig. 2 experience Optimizing Flows.
Fig. 3 is algorithm global optimizing flow.
Fig. 4 is mass change in embodiment optimization process.
Fig. 5 is that maximum stress changes in embodiment optimization process.
Specific implementation mode
With reference to the accompanying drawings and examples, the following further describes the technical solution of the present invention.
The present invention proposes a kind of unmanned helicopter fuselage interior structural optimization method, as shown in Figure 1, specifically including following step
Suddenly：
Step 1: establishing the finite element model of fuselage interior structure
The entirety of the mounting means and mounting structure of Aerial Electronic Equipment is had determined that in the design phase of fuselage interior structure
Frame, the Optimization Work that the present invention designs are carried out mainly for the size of mounting structure.Nobody is gone straight up to curved surface and wire frame
Machine fuselage interior structure carries out simplifying modeling, replaces the sheet material portions such as frame, panel with curved surface, steelframe and rib are replaced with wire frame
Equal proximate matters part, is simulated curved surface, is simulated wire frame with beam in corresponding finite element model with plate shell.Due to fuselage interior knot
Structure is connected in fuselage main body structure, and connection type can be divided into clamped connection and hinged two kinds of connection, in above-mentioned finite element
It needs to apply the boundary condition in finite element model respectively according to the connection type in practical structures in model.
Step 2: determining outer carry
The overload production that the stress of unmanned helicopter internal structure is brought essentially from the gravity and flare maneuver of Aerial Electronic Equipment
Raw additional force, since the additional force overload that can be used uniformly all related with Aerial Electronic Equipment quality of gravity and overload generation carrys out table
Show, needs to consider respectively up and down the overload in 6 directions all around.Take the centroid position of each Aerial Electronic Equipment as load(ing) point,
It can determine the size of power and torque in outer carry completely using overload factor, each equipment quality, equipment centroid position.Its
In, the product of overload factor and equipment quality is exactly the stress size of equipment, Impact direction along overload direction；According to step
One connection relation determined, equipment stress is transmitted in fuselage interior structure to be optimized, generates the effect of power and torque.
Step 3: choosing Optimal Parameters
In order to be optimized to system structure, to reduce stress raisers and total quality, chooses beam element and cut
The thickness in face parameter as an optimization, with structural stress index as an optimization, meet allowed in certain range of stress section thickness most
It is small so that construction weight is most light.To same structure, under same outer carry, the smaller internal stress of section thickness is bigger,
Stress excessive component needed to increase thickness reduce stress, for the component of understressing should reduce thickness mitigate
Construction weight, final realize need to use construction weight minimum under stress index.
Step 4: carrying out structure optimization calculating
Use experience optimization is optimized with optimization algorithm global optimizing combined method.
Experience optimization is carried out first.Analysis and summary is carried out to the stress state under different overload situations, it is rule of thumb right
The wherein larger position of stress suitably increases thickness, for the appropriate reduced thickness in stress smaller part position, re-starts calculating, obtains new
Model weight and stress state, if model weight mitigates and model maximum stress is less than allowable value, iteration success is being repaiied
Change and continues iteration optimization on the basis of rear model；Otherwise iteration fails, then continues iteration optimization, this mode on the basis of master mould
Suitable for designing initial stage, construction weight is quickly reduced based on designer's experience.Detailed process is as shown in Fig. 2.
Then algorithm global optimizing is optimized.There is coupling in the influence due to each Optimal Parameters to structural stress state
Effect, adjustment thickness parameter may cause to find less than meeting the combination parameter of material allowable value, thus use instead optimization algorithm into
Row global optimizing.Under this approach, total lightest for optimization aim with structure by giving each parameter value range, it uses
The parametric modeling method fast and automatically modeling of finite element software simultaneously solves, and result is fed back to optimization algorithm end, by calculating
Method selects suitable combination parameter to be iterated optimizing.Detailed process is as shown in Fig. 3.Common optimization algorithm has gradient decline
The heuristic values such as the traditional algorithms such as method, Newton method and simulated annealing, genetic algorithm.The usual base of traditional algorithm
The relationship between variables and objective function, it is close to optimal solution by way of Step wise approximation；And heuritic approach does not need
The relationship between variables and objective function is solved, thus there is better applicability, is usually also required to more iterations.
Embodiment
Certain type unmanned helicopter research and development program element, fuselage interior structure optimization has been carried out using the above method.First, in accordance with step
Rapid one, the requirement of step 2 establishes simplified structure and outer load model in ABAQUS finite element modeling softwares, chooses vertical
5g, other directions 2g overload as outer load；Then, the thickness of 16 beam models in fuselage interior structure is chosen according to step 3
It is worth parameter as an optimization, it is determined that optimization direction keeps construction weight most light for the limiting range of stress in 183MPa；Finally according to step
Four perform experience optimization and the algorithm optimization based on ISIGHT optimization softwares respectively.
Mass change in optimization process is shown in attached drawing 4.
Attached drawing 5 is shown in maximum stress variation in optimization process.
The result shows that the method proposed in through the invention, it can be under the premise of ensureing enough structural strengths significantly
Mitigate construction weight.
Claims (3)
1. a kind of unmanned helicopter fuselage interior structural optimization method, it is characterised in that：This method specifically comprises the following steps：
Step 1: establishing the finite element model of fuselage interior structure
Unmanned helicopter fuselage interior structure is carried out with curved surface and wire frame to simplify modeling, sheet material portions is replaced with curved surface, uses line
Frame replaces proximate matter part, is simulated curved surface with plate shell in corresponding finite element model, is simulated wire frame with beam；Due in fuselage
Portion's structure is connected in fuselage main body structure, and connection type can be divided into clamped connection and hinged two kinds of connection, have above-mentioned
It needs to apply the boundary condition in finite element model respectively according to the connection type in practical structures in limit meta-model；
Step 2: determining outer carry
What the overload that the stress of unmanned helicopter internal structure is brought essentially from the gravity and flare maneuver of Aerial Electronic Equipment generated
Additional force, the additional force generated due to gravity and overload is all related with Aerial Electronic Equipment quality can be used uniformly overload and indicates,
Need to consider respectively all around overload in 6 directions up and down；It takes the centroid position of each Aerial Electronic Equipment as load(ing) point, utilizes
Overload factor, each equipment quality, equipment centroid position can determine the size of outer power and torque in carrying completely；
Step 3: choosing Optimal Parameters
In order to be optimized to system structure, to reduce stress raisers and total quality, beam element section is chosen
Thickness parameter as an optimization, with structural stress index as an optimization, meet allowed in certain range of stress section thickness minimum from
And make construction weight most light；To same structure, under same outer carry, the smaller internal stress of section thickness is bigger, for
Stress excessive component needs to increase thickness reduces stress, for the component of understressing should reduce thickness mitigate structure
Weight, final realize need to use construction weight minimum under stress index；
Step 4: carrying out structure optimization calculating
Use experience optimization is optimized with optimization algorithm global optimizing combined method；
Experience optimization is carried out first；Analysis and summary is carried out to the stress state under different overload situations, rule of thumb to wherein
The larger position of stress suitably increases thickness, for stress smaller part position reduced thickness, re-starts calculating, obtains new model weight
Amount and stress state, if model weight mitigates and model maximum stress is less than allowable value, iteration is successful, after the modification model
On the basis of continue iteration optimization；Otherwise iteration fails, then continues iteration optimization on the basis of master mould；
Then algorithm global optimizing is optimized；It is total lightest for optimization aim with structure by giving each parameter value range,
Using finite element software parametric modeling method fast and automatically modeling and solve, result is fed back into optimization algorithm end,
Optimizing is iterated by the suitable combination parameter of algorithms selection.
2. a kind of unmanned helicopter fuselage interior structural optimization method according to claim 1, it is characterised in that：The step
In rapid two, the product of overload factor and equipment quality is the size of equipment stress, Impact direction along overload direction；According to step
Equipment stress, is transmitted in fuselage interior structure to be optimized by rapid one connection relation determined according to the transfer principle of power, produces
The effect of raw power and torque.
3. a kind of unmanned helicopter fuselage interior structural optimization method according to claim 1, it is characterised in that：The step
Optimization algorithm in rapid four includes that gradient descent method, the traditional algorithm of Newton method and simulated annealing, genetic algorithm open
Hairdo optimization algorithm.
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Application publication date: 20181016 |