CN110610048A - Dynamic load factor calculation method for eccentric impact test - Google Patents
Dynamic load factor calculation method for eccentric impact test Download PDFInfo
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- CN110610048A CN110610048A CN201910882743.9A CN201910882743A CN110610048A CN 110610048 A CN110610048 A CN 110610048A CN 201910882743 A CN201910882743 A CN 201910882743A CN 110610048 A CN110610048 A CN 110610048A
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The application belongs to the field of design of structural strength of airplanes, and particularly relates to a dynamic load factor calculation method for an eccentric impact test. The method comprises the following steps: acquiring static displacement of a test piece and a deck impact contact point under the action of a preset static load; acquiring impact kinetic energy of a test piece when an airplane lands on a ship at a preset sinking speed; acquiring strain energy of the test piece when the preset static load acts on the deck according to the static displacement of the impact contact point of the test piece and the deck; and calculating the dynamic load factor of the eccentric impact deck of the test piece according to the impact kinetic energy of the test piece and the strain energy of the test piece. The dynamic load factor calculation method aiming at the eccentric impact test is simple and concise, the obtained dynamic load factor and impact load result are high in goodness of fit with the result of the test flight actual measurement data, the dynamic load factor K is firstly calculated, and the dynamic impact load F can be conveniently calculated by utilizing the multiple relation of the dynamic load and the static load.
Description
Technical Field
The application belongs to the field of design of structural strength of airplanes, and particularly relates to a dynamic load factor calculation method for an eccentric impact test.
Background
In the field of aircraft structural strength design, a test piece needs to calculate the dynamic impact load impacting a deck in an eccentric state. In the prior art, a method for calculating the dynamic impact load of a test piece impacting a deck in an eccentric state is complex and cannot be well consistent with a test flying test result.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a dynamic load factor calculation method for an eccentric impact test, so as to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
a dynamic load factor calculation method for an eccentric impact test, comprising:
acquiring static displacement of a test piece and a deck impact contact point under the action of a preset static load;
acquiring impact kinetic energy of a test piece when an airplane lands on a ship at a preset sinking speed;
acquiring strain energy of the test piece when the preset static load acts on the deck according to the static displacement of the impact contact point of the test piece and the deck;
and calculating the dynamic load factor of the eccentric impact deck of the test piece according to the impact kinetic energy of the test piece and the strain energy of the test piece.
Optionally, in obtaining the static displacement of the impact contact point of the test piece and the deck under the action of the predetermined static load, the static displacement of the impact contact point of the test piece and the deck is:
wherein, δ is the static displacement of the impact contact point of the test piece and the deck, Q is the static load of the test piece, L is the length of the test piece, S is the impact eccentricity, E is the Young modulus of the material of the test piece, and G is the shear modulus of the material of the test piece.
Optionally, in the obtaining of the impact kinetic energy of the test piece when the aircraft lands at the preset sinking speed, the impact kinetic energy of the test piece is:
wherein A is the impact kinetic energy of the test piece, M is the mass of the test piece, and v is the sinking speed of the airplane.
Optionally, the obtaining of the strain energy of the test piece when the predetermined static load acts on the deck according to the static displacement of the impact contact point of the test piece with the deck may be:
wherein, U is the strain energy of the test piece, M is the test piece mass, g is the acceleration of gravity, and delta is the static displacement of the impact contact point of the test piece and the deck.
Optionally, in the calculating the dynamic load factor of the test piece eccentrically impacting the deck according to the impact kinetic energy of the test piece and the strain energy of the test piece, the dynamic load factor of the test piece eccentrically impacting the deck is as follows:
k is a dynamic load factor of the eccentric impact of the test piece on the deck, v is the sinking speed of the airplane, g is the gravity acceleration, and delta is the static displacement of the impact contact point of the test piece and the deck.
Optionally, the structural model of the test piece eccentric impact deck is a cantilever beam.
Optionally, the test piece material is high strength steel.
The invention has at least the following beneficial technical effects:
according to the dynamic load factor calculation method for the eccentric impact test, the dynamic load factor is simply and concisely calculated, and the obtained dynamic load factor and impact load result are high in goodness of fit with the result of the test flight actual measurement data.
Drawings
FIG. 1 is a schematic view of a specimen off-center impact deck loaded according to one embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1.
The application provides a dynamic load factor calculation method for an eccentric impact test, which comprises the following steps:
acquiring static displacement of a test piece and a deck impact contact point under the action of a preset static load;
acquiring impact kinetic energy of a test piece when an airplane lands on a ship at a preset sinking speed;
acquiring strain energy of the test piece when a preset static load acts on the deck according to the static displacement of an impact contact point of the test piece and the deck;
and calculating the dynamic load factor of the eccentric impact deck of the test piece according to the impact kinetic energy and the strain energy of the test piece.
Specifically, the structural model can be simplified into a cantilever beam, and the static displacement δ of the impact contact point P between the test piece and the deck under the action of the static load Q is firstly calculated, and the formula is as follows:
wherein, delta is the static displacement of the impact contact point of the test piece and the deck, and the unit is m; q is the static load of the test piece and is in the unit of N; l is the length of the test piece and is m; s is the impact eccentricity, and the unit is m; e is the Young's modulus of the test piece material and has the unit of N/m2(ii) a G is the shear modulus of the material of the test piece, and the unit is N/m2。
Then, the impact kinetic energy A of the test piece when the aircraft lands on the ship at the sinking speed v is obtained, and the formula is as follows:
wherein A is the impact kinetic energy of the test piece and the unit is J; m is the mass of the test piece in kg; v is the aircraft sinking velocity in m/s.
Further, the strain energy U of the test piece when acting on the deck with a static load Q is obtained according to the static displacement delta of the impact contact point of the test piece and the deck, and the formula is as follows:
wherein U is the strain energy of the test piece and the unit is J; m is the mass of the test piece in kg; g is the acceleration of gravity in m/s2(ii) a δ is the static displacement of the point of impact contact of the test piece with the deck in m.
And finally, calculating a dynamic load factor K of the eccentric impact deck of the test piece according to the impact kinetic energy A and the strain energy U of the test piece, wherein the formula is as follows:
k is a dynamic load factor of the eccentric impact deck of the test piece; v is the sinking speed of the airplane and the unit is m/s; g is the acceleration of gravity in m/s2(ii) a δ is the static displacement of the point of impact contact of the test piece with the deck in m.
In one embodiment of the present application, in a test piece of a certain type of ship-based aircraft, the hook bar material is high-strength steel 30CrMnSiNi2A, and the young's modulus E of the steel is 1.95 × 1011N/m2Shear modulus G ═ 7.5X 1010N/m2. The cross section of the hook rod is a hollow circular ring which can be equivalently that the outer diameter D is 0.11M and the inner diameter D is 0.08M, the length of the hook rod is 2M, and the mass M is 70 kg.
The following sinking speed v of the shipboard aircraft is 5.5m/S, when the impact eccentricity S of a test piece and a deck is 0.05m, firstly, a structural model is simplified into a cantilever beam, and the static displacement delta of an impact contact point P of the test piece and the deck under the action of a static load Q is calculated as follows:
in the formula, delta is the static displacement of the impact contact point of the test piece and the deck, and the unit is m; q is the static load of the test piece and is in the unit of N; l is the length of the test piece and is m; s is the impact eccentricity, and the unit is m; e is the Young's modulus of the test piece material and has the unit of N/m2(ii) a G is the shear modulus of the material of the test piece, and the unit is N/m2。
Then, the dynamic load factor K of the test piece eccentric impact deck is as follows:
wherein v is the sinking speed of the airplane and the unit is m/s; g is the acceleration of gravity in m/s2(ii) a Delta is test piece and deckThe static displacement of the point of impact contact is in m.
The dynamic load factor calculation method aiming at the eccentric impact test is simple and concise, the obtained dynamic load factor and impact load result are high in goodness of fit with the result of the test flight actual measurement data, the dynamic load factor K is firstly calculated, the dynamic impact load F can be conveniently calculated by utilizing the multiple relation of the dynamic load and the static load, and the dynamic load factor calculation method is generally suitable for the field of design of airplane structural strength.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A dynamic load factor calculation method for an eccentric impact test, comprising:
acquiring static displacement of a test piece and a deck impact contact point under the action of a preset static load;
acquiring impact kinetic energy of a test piece when an airplane lands on a ship at a preset sinking speed;
acquiring strain energy of the test piece when the preset static load acts on the deck according to the static displacement of the impact contact point of the test piece and the deck;
and calculating the dynamic load factor of the eccentric impact deck of the test piece according to the impact kinetic energy of the test piece and the strain energy of the test piece.
2. The method for calculating the dynamic load factor for the eccentric impact test according to claim 1, wherein the static displacement of the impact point of the test piece and the deck under the action of the predetermined static load is obtained by:
wherein, δ is the static displacement of the impact contact point of the test piece and the deck, Q is the static load of the test piece, L is the length of the test piece, S is the impact eccentricity, E is the Young modulus of the material of the test piece, and G is the shear modulus of the material of the test piece.
3. The method for calculating the dynamic load factor for the eccentric impact test according to claim 2, wherein in the step of obtaining the impact kinetic energy of the test piece when the aircraft lands at the preset sinking speed, the impact kinetic energy of the test piece is as follows:
wherein A is the impact kinetic energy of the test piece, M is the mass of the test piece, and v is the sinking speed of the airplane.
4. The method for calculating the dynamic load factor for the eccentric impact test according to claim 3, wherein the strain energy of the test piece when the predetermined static load acts on the deck is obtained from the static displacement of the impact contact point of the test piece with the deck, and the strain energy of the test piece is:
wherein, U is the strain energy of the test piece, M is the test piece mass, g is the acceleration of gravity, and delta is the static displacement of the impact contact point of the test piece and the deck.
5. The method for calculating the dynamic load factor for the eccentric impact test according to claim 4, wherein in the calculating the dynamic load factor of the eccentric impact deck of the test piece according to the impact kinetic energy of the test piece and the strain energy of the test piece, the dynamic load factor of the eccentric impact deck of the test piece is as follows:
k is a dynamic load factor of the eccentric impact of the test piece on the deck, v is the sinking speed of the airplane, g is the gravity acceleration, and delta is the static displacement of the impact contact point of the test piece and the deck.
6. The method for calculating the dynamic load factor for the eccentric impact test according to claim 1, wherein the structural model of the test piece eccentric impact deck is a cantilever beam.
7. The method for calculating the dynamic load factor for the eccentric impact test according to claim 6, wherein the test piece material is high-strength steel.
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