CN110737949A - Emission stress analysis method for folding wings of barrel type emission unmanned aerial vehicle - Google Patents
Emission stress analysis method for folding wings of barrel type emission unmanned aerial vehicle Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
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Abstract
The invention discloses an launching stress analysis method for folding wings of a barrel type launching unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicle launching and comprises the steps of S1 establishing a wing coordinate system, S2 determining a geometric relation of each position of the wings in the launching process of the wings in a barrel, S3 determining force and moment borne by the wings according to the geometric position relation of the wing coordinate system and the wings, S4 determining deformation generated by the wings according to the stress condition of the wings and determining the position of maximum deformation of the wings, S5 determining critical load borne by the wings, S6 determining stress borne by the wings, and determining deformation, maximum deformation position, critical load and stress generated by the wings in the launching process of the wings in the barrel through stress analysis in the launching process of the wings in the barrel, so that whether the folding wings of the unmanned aerial vehicle are safely and reliably unfolded after the folding wings are out of the barrel can be rapidly judged, and a reliable mechanical basis is provided for optimization design and safety check of the folding wings of the barrel type launching unmanned aerial vehicle.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle launching, in particular to an analysis method for launching stress of folded wings of cylindrical launching unmanned aerial vehicles.
Background
The cylinder type launching unmanned aerial vehicle is generally designed in a storage and transportation integration mode, wings of the unmanned aerial vehicle are folded and loaded in a launching cylinder during normal service and are transported or carried integrally, during operation, a gas generator at the bottom of the launching cylinder generates high-pressure gas to push the unmanned aerial vehicle to move in the cylinder in an accelerated mode, the unmanned aerial vehicle rapidly expands the wings to fly after exiting the cylinder and starts to perform operation tasks, no restriction is performed during folding of the wings of the unmanned aerial vehicle, and a mounting gap of is reserved between the wings and the launching cylinder, so that the folded wings of the unmanned aerial vehicle in a loading state can be freely unfolded under the action of a torsion spring at the wing root, wing tips and the cylinder wall are mutually extruded under the action of gas thrust and extrusion force of the cylinder wall during launching, the folded wings bear constant pressure and bending moment to influence the rigidity and strength of the folded wings, and hidden danger is caused by safe and reliable expansion of the folded wings of the unmanned aerial vehicle after exiting the wings.
Disclosure of Invention
The invention aims to solve the problems and designs methods for analyzing the launching stress of folding wings of a cylindrical launching unmanned aerial vehicle.
The invention realizes the purpose through the following technical scheme:
A method for analyzing launching stress of folding wings of a cylindrical launching unmanned aerial vehicle comprises the following steps:
s1, establishing a wing coordinate system, taking a wing rotating axis as a coordinate origin o, taking an o-passing point as a transverse plane of the launching tube, taking an o-passing point as a tangent plane parallel to a longitudinal plane of the launching tube, wherein the tangent plane is vertical to the transverse plane of the launching tube, the intersecting line of the two planes is an oX axis, defining the right wall surface pointing to the launching tube as the positive direction of the oX axis, taking a perpendicular line vertical to the oX in the tangent plane passing the o-passing point and parallel to the longitudinal plane of the launching tube, obtaining a oY axis, and defining the pointing launching direction as the positive direction of oY;
s2, determining a geometric relational expression of each position of the wing in the process of launching the wing in the barrel;
s3, determining the force and moment applied to the wing in the process of launching in the cylinder according to the geometrical position relationship between the wing coordinate system and the wing;
s4, determining the deformation of the wings in the launching process of the wings in the barrel according to the stress condition of the wings, and determining the position of the maximum deformation of the wings;
s5, determining the critical load borne by the wing in the process of launching the wing in the barrel;
and S6, determining the stress borne by the wing in the launching process in the barrel.
The invention has the beneficial effects that: through the stress analysis of the wings in the launching process in the barrel, the deformation, the maximum deformation position, the borne critical load and the stress generated by the wings in the launching process in the barrel can be determined, whether the folded wings of the unmanned aerial vehicle are safely and reliably unfolded after being taken out of the barrel can be quickly judged, and reliable mechanical basis is provided for the optimized design and safety check of the folded wings of the barrel-type launching unmanned aerial vehicle.
Drawings
Fig. 1 is a schematic view of wing stress of an method for analyzing launching stress of folding wings of a barrel-type launching unmanned aerial vehicle;
FIG. 2 is a schematic diagram of the deformation angle associated with the torsion spring during the wing opening process in the analysis method for the launching force of the folding wing of kinds of barrel-type launch unmanned aerial vehicles according to the invention;
fig. 3 is a stress schematic diagram of a simplified simply supported beam of an airfoil in the launch stress analysis method of folding airfoils of a drum launch unmanned aerial vehicle of the invention.
Detailed Description
To further clarify the objects, aspects and advantages of embodiments of the present invention, a more complete description of embodiments of the present invention is now provided by reference to the drawings which form a part hereof.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. 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 invention.
It should be noted that like reference numerals and letters refer to like items in the following figures, and thus once a item is defined in figures, it need not be further defined and explained by in subsequent figures.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "inside", "outside", "left", "right", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or the orientations or positional relationships that the products of the present invention are conventionally placed in use, or the orientations or positional relationships that are conventionally understood by those skilled in the art, and are used for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
Moreover, the terms "," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed" and "connected" and the like shall be used , for example, "connected" may be a fixed connection, a detachable connection, or body connection, a mechanical connection, an electrical connection, a direct connection, an indirect connection via an intermediate medium, and communication between two elements.
The following detailed description of embodiments of the invention refers to the accompanying drawings.
The invention is further described with reference to the following drawings:
A method for analyzing launching stress of folding wings of a cylindrical launching unmanned aerial vehicle comprises the following steps:
s1, establishing a wing coordinate system, as shown in figure 1, taking a wing rotating shaft center as a coordinate origin o, taking an o passing point as a transverse plane of the launching tube, taking an o passing point as a tangent plane parallel to a longitudinal plane of the launching tube, wherein the tangent plane is perpendicular to the transverse plane of the launching tube, the intersecting line of the two planes is an oX axis, defining the right wall surface of the pointed launching tube as the positive direction of the oX axis, and taking a perpendicular line perpendicular to the oX in the tangent plane which passes the o passing point and is parallel to the longitudinal plane of the launching tube to obtain oY axes, and defining the pointed launching direction as the positive direction of oY;
s2, as shown in fig. 1 and 2, determining a geometric relation of each position of the wing during the launching process of the wing in the canister, where the geometric relation of each position of the wing includes: phi is a2＝φ1+φ、
φe＝φs-φ1+φ0Wherein phi is1Is the wing deflection angle, rad; phi is a2The included angle between the connecting line from the contact point of the wall of the cylinder to the center of the rotating shaft of the wing tip and the oY axis, rad; phi is the included angle between the connecting line from the contact point of the cylinder wall to the center of the wing rotating shaft and the center line of the right rear wing, rad;theta is the included angle between the connecting line of the contact point of the wing tip on the inner wall of the cylinder and the center of the rotating shaft of the missile wing and the X axis, and rad; rfIs the radius of the inner cavity of the launch canister, m; l isWIs wing length, m; bWIs the right rear chord length, m; phi is asThe angle phi between the extension direction and the Y axis after the wing is unfolded in place1Is the angle of spread phi0The torsional deformation angle phi of the torsion spring in the state that the wing pieces are opened in placeeIs the torsional deformation angle of the torsion spring;
s3, determining the force and moment applied to the wing in the process of launching in the cylinder according to the geometrical position relationship between the wing coordinate system and the wing;
calculating the air resistance and air resistance moment of the wing in the launching process in the cylinder, wherein the air resistance after the wing is inclined isAssuming the resultant air resistance force action point is at the geometric midpoint of the airfoil, XWMoment to o point is
In the formula, XWIs the air resistance, N; rho is air density, kg/m3(ii) a V is the speed of the flight patrol at the maximum transmission overload moment, m/s; cxwIs an air resistance coefficient of to a straight wing as a reference area, S'WIs the missile wing area, M, M of wingsXwIs the air resistance moment, N.m;
calculating torsion spring pressure and torsion applied to the wing in the process of launching in the cylinder, and assuming that the included angle between the extension direction and the Y axis is phi after the wing is unfolded in placesThe angle of spread is phi1The torsion spring has a torsion deformation angle phi of in the state that the wing pieces are opened to the proper positions0The torsional deformation angle phi of the torsion springeIs phie＝φs-φ1+φ0The torsion of the torsion spring is
Assuming that the torsion of the torsion spring acts perpendicularly on the wing side surface, the pressure of the torsion spring is
In the formula, MeTorsion spring torque, N.m; esIs the elastic modulus, Pa, of the spring material; d2Is the diameter of the spring wire, m; n is the effective working turns of the torsion spring; d2The pitch diameter of the torsion spring is m; b is the distance m from the action point of the torsion spring to the center of the rotating shaft;
calculating the inertia force and the inertia moment of the wing in the launching process in the barrel, wherein the inertia force of the wing in the launching process in the barrel is Fa＝m1a, assuming that the action point of the inertia force is at the center of mass of the airfoil, the moment of the inertia force to the point o is
Wherein the wing mass is m1The maximum launching acceleration in the cylinder is a;
s4, determining the deformation of the wings in the launching process of the wings in the barrel according to the stress condition of the wings, and determining the position of the maximum deformation of the wings;
s41, assuming that the wall surface of the launching tube is smooth and the wall surface of the launching tube is parallel to the Y axis, therefore, the friction force and the tangential force between the wing tip and the tube wall are ignored, and according to the statics principle, the balance relation of the force and the moment is obtained as follows:
s42, as shown in figure 3, the wing is simplified into a simple beam without considering the wing profile, only the transverse stress is considered, and the displacement equation of the wing at different positions from the center of the rotating shaft is obtained by the general equation of the linear elastic beam
The lower part of the right side of the equation is marked with I, II and III to represent different stressed subareas of the wing;
s43, Z pairs in different stress zones1Obtaining the maximum deformation position of the wing by derivation;
1) when analyzing the deformation of the region I, the right side of the equation is only subscripted I (subscripted II, III are not required), and thenThen to Z1Derivation is carried out;
2) when analyzing the deformation of region II, the right side of the equation is only subscripted to the formulas I and II (subscripted to the unnecessary formula III), and then Z is again subjected to1Derivation is carried out;
3) when analyzing the deformation of the III region, the right side of the equation is all needed, and then Z is processed1Derivation is carried out;
s5, determining the critical load borne by the wing in the process of launching in the cylinder, wherein the stability of the wing under compression is represented as the critical load
In the formula, PLCritical load, E is the modulus of elasticity, Pa, of the wing material; j. the design is a squarex1Wing section minimum moment of inertia;
s6, determining the stress borne by the wing in the launching process in the barrel, and considering only the longitudinal stress, wherein the stress borne by the wing in the launching process in the barrel is axial stress and is expressed as
Wherein σ is axial stress, Pa; s is the cross section of the wing along the chord length direction, m2。
The method is suitable for the launching stress analysis of the folding wings of the barrel-type launching unmanned aerial vehicle, provides a calculation method for the rigidity and the strength of the folding wings of unmanned aerial vehicles in the launching process in the barrel, can determine the deformation, the maximum deformation position, the borne critical load and the stress of the wings in the launching process of the wings in the barrel through the stress analysis of the wings in the launching process in the barrel, is beneficial to quickly judging whether the folding wings of the unmanned aerial vehicle are safely and reliably unfolded after being taken out of the barrel, and can provide reliable mechanical basis for the optimized design and the safety check of the folding wings of the barrel-type launching unmanned aerial vehicle.
The technical solution of the present invention is not limited to the limitations of the above specific embodiments, and all technical modifications made according to the technical solution of the present invention fall within the protection scope of the present invention.
Claims (6)
1, kinds of cartridge type launch unmanned aerial vehicle folding wing launch force analysis method, characterized by, including the following steps:
s1, establishing a wing coordinate system, taking a wing rotating axis as a coordinate origin o, taking an o-passing point as a transverse plane of the launching tube, taking an o-passing point as a tangent plane parallel to a longitudinal plane of the launching tube, wherein the tangent plane is vertical to the transverse plane of the launching tube, the intersecting line of the two planes is an oX axis, defining the right wall surface pointing to the launching tube as the positive direction of the oX axis, taking a perpendicular line vertical to the oX in the tangent plane passing the o-passing point and parallel to the longitudinal plane of the launching tube, obtaining a oY axis, and defining the pointing launching direction as the positive direction of oY;
s2, determining a geometric relational expression of each position of the wing in the process of launching the wing in the barrel;
s3, determining the force and moment applied to the wing in the process of launching in the cylinder according to the geometrical position relationship between the wing coordinate system and the wing;
s4, determining the deformation of the wings in the launching process of the wings in the barrel according to the stress condition of the wings, and determining the position of the maximum deformation of the wings;
s5, determining the critical load borne by the wing in the process of launching the wing in the barrel;
and S6, determining the stress borne by the wing in the launching process in the barrel.
2. The method for analyzing the launching force of the folding wing of cylinder type launching unmanned aerial vehicle of claim 1, wherein in S2, the geometrical relation of each position of the wing includes phi2＝φ1+φ、
φe＝φs-φ1+φ0Wherein phi is1Is the wing deflection angle, rad; phi is a2The included angle between the connecting line from the contact point of the wall of the cylinder to the center of the rotating shaft of the wing tip and the oY axis, rad; phi is the included angle between the connecting line from the contact point of the cylinder wall to the center of the wing rotating shaft and the center line of the right rear wing, rad; theta is the contact point of the wing tip on the inner wall of the cylinder and the rotating shaft of the missile wingThe angle between the central connecting line and the X axis, rad; rfIs the radius of the inner cavity of the launch canister, m; l isWIs wing length, m; bWIs the right rear chord length, m; phi is asThe angle phi between the extension direction and the Y axis after the wing is unfolded in place1Is the angle of spread phi0The torsional deformation angle phi of the torsion spring in the state that the wing pieces are opened in placeeIs the torsional deflection angle of the torsion spring.
3. The method for analyzing launching force of folding wings of kinds of cartridge launching unmanned aerial vehicles according to claim 2, wherein in S3, the force applied to the wings during launching of the wings in the cartridges includes air resistance XWTorsion spring pressure T and inertia force FaThe moment applied to the wing during the launch in the canister comprises an air drag moment MXwTorsion M of torsion springeAnd moment of inertia MaThe air flow is controlled, according to the aerodynamic principle,
Fa＝m1a，
where ρ is the air density, kg/m3(ii) a V is the speed of the flight patrol at the maximum transmission overload moment, m/s; cxwIs an air resistance coefficient of to a straight wing as a reference area, S'WIs the missile wing area, m, E, of wingssIs the elastic modulus, Pa, of the spring material; d2Is the diameter of the spring wire, m; n is the effective working turns of the torsion spring; d2The pitch diameter of the torsion spring is m; and b is the distance m from the action point of the torsion spring to the center of the rotating shaft.
4. The method for analyzing launching force of folding wings of kinds of cartridge launching drones according to claim 3, wherein in S4, the method comprises the following steps:
s41, pressing to quietThe balance relation of the obtained force and the moment is as follows according to the mechanics principle:
s42, determining displacement equations of different positions of the wing from the center of the rotating shaft through a general equation of the linear elastic beam as
S43, Z pairs in different stress zones1And (5) obtaining the position of the maximum deformation of the wing by derivation.
5. The method for analyzing launching stress of folding wings of cartridge launch unmanned aerial vehicle of claim 4, wherein in S5, the critical load borne by the wings during launching of the wings in the cartridges is
Wherein, PLCritical load, E is the modulus of elasticity, Pa, of the wing material; j. the design is a squarex1The minimum moment of inertia of the airfoil section.
6. The method for analyzing launching stress of folding wings of cartridge launch unmanned aerial vehicle of claim 5, wherein in S6, only longitudinal stress is considered, and the stress borne by the wings during launching in the cartridge is axial stress
σ is axial stress, Pa; s is the cross section of the wing along the chord length direction, m2。
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| 陈佳等: "某型飞机机翼弯曲变形的仿真计算", 《机电工程》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112985674A (en) * | 2021-01-26 | 2021-06-18 | 河北汉光重工有限责任公司 | Rolling torque measuring method of folding missile wing combination |
| CN112985675A (en) * | 2021-01-26 | 2021-06-18 | 河北汉光重工有限责任公司 | Folding missile wing torque measuring method |
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