CN114111461A - Three-dimensional negative-stiffness elastic frame - Google Patents
Three-dimensional negative-stiffness elastic frame Download PDFInfo
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- CN114111461A CN114111461A CN202111472286.XA CN202111472286A CN114111461A CN 114111461 A CN114111461 A CN 114111461A CN 202111472286 A CN202111472286 A CN 202111472286A CN 114111461 A CN114111461 A CN 114111461A
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
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Abstract
A three-dimensional negative-stiffness elastic frame belongs to the technical field of aircraft deformation and solves the problem that an existing rocket controlled by a deflection head is large in energy consumption; the cylinder can be a cylinder, an elliptic cylinder, a square cylinder, a polygonal cylinder and the like or a cylinder with any shape such as a straight cylinder, a bent cylinder, a reducer cylinder and the like, and can be arranged according to the head requirement of the aircraft; because the cylinder wall is provided with the hollow parts which are arranged in a shape like a Chinese character 'pin' and is arranged along the circumferential direction of the cylinder wall, the cylinder wall can have the function of elastic deformation along the axial direction like a spring, thereby realizing integral deflection; the above is the prior art; the cylinder wall reserved around each hollow in the triangular arrangement comprises a top beam, a bottom beam and a curved beam protruding outwards or inwards, wherein the top beam and/or the bottom beam reserved around each hollow in the triangular arrangement of the vertical beams on the two sides are/is convex or concave; the invention is used for aircraft deformation.
Description
Technical Field
The invention belongs to the technical field of aircraft deformation, and particularly relates to a three-dimensional negative-stiffness elastic frame.
Background
Flight control of aircrafts such as a common rocket is mainly realized through an empennage and a duck rudder, the duck rudder positioned at the head of the rocket can rotate through a rudder piece to change the aerodynamic control flight attitude, but the duck rudder is easily influenced by shock waves at the head of the rocket, so that the control efficiency is reduced, and the existence of the duck rudder can increase the resistance of a projectile body and interfere the empennage, thereby causing adverse effect on the flight control.
The deflection head control mode is a unique rocket control mode, and can generate control torque by changing an included angle between the head and the axis of the rocket and by the pressure difference between the windward side and the leeward side of the rocket, so that the aim of controlling the rocket to fly flexibly is fulfilled. In 1946, the invention provides the rocket with the rotatable head and the rotatable tail wing, and improves the mechanical connection performance of the head of the rocket and the projectile body, so that the rocket can adjust the trajectory by changing the angles of the head and the tail in the high-speed flight process; by comparing the influence of the deflection head and the traditional canard control mode on the aerodynamic performance of the rocket and the pitching control efficiency of the deflection head and the traditional canard control mode through wind tunnel tests with Mach numbers of 3.0 and 6.0, the advantages of high control efficiency of the deflection head, small resistance, strong maneuvering performance and the like are obtained; aerodynamic force borne by the aircraft under the conditions of different head deflection angles, different Mach numbers and different attack angles of a deflection head rocket is simulated through Fluent software, and the aircraft can obtain larger lift-drag ratio and yaw moment due to the existence of the head deflection angle; a dynamic model of the deflection head rocket is established by adopting a Schiehlen method, and the deflection head rocket is verified to have the advantages of high control efficiency, large maneuvering overload, high response speed and the like through simulation.
However, the rocket controlled by the deflection head has the problems that the larger the deflection angle is, the larger the required driving force is, and the larger the consumed energy is. For example, the invention patent with the publication number of CN113267092A discloses a technology for realizing warhead deformation through a deformable skeleton, which presents a positive stiffness effect in the structural deformation process, and the bending moment in the deflection process is continuously increased along with the increase of the angle, consuming a large amount of energy.
Disclosure of Invention
The invention aims to solve the problems that the larger the deflection angle of a rocket controlled by a deflection head is, the larger the required driving force is and the larger the consumed energy is, and provides a three-dimensional negative-stiffness elastic frame, which has the following technical scheme:
a three-dimensional negative-stiffness elastic frame comprises a cylinder wall provided with a plurality of hollows, wherein the hollows are arranged in a delta shape, and the left and right directions of the delta shape are arranged along the circumferential direction of the cylinder wall; the cylinder can be a cylinder, an elliptic cylinder, a square cylinder, a polygonal cylinder and the like or a cylinder with any shape such as a straight cylinder, a bent cylinder, a reducer cylinder and the like, and can be arranged according to the head requirement of the aircraft; because the cylinder wall is provided with the hollow parts which are arranged in a shape like a Chinese character 'pin' and is arranged along the circumferential direction of the cylinder wall, the cylinder wall can have the function of elastic deformation along the axial direction like a spring, thereby realizing integral deflection; the above is the prior art; the cylinder wall reserved around each hollow in the triangular arrangement comprises a top beam, a bottom beam and vertical beams at two sides, namely four beams which are enclosed into a square shape; the top beams and/or the bottom beams which are arranged in a triangle shape and are retained around each hollow-out are convex or concave curved beams; the outward convex curved beam is divided into two stages by the inward deformation process under pressure, the former stage is a stage from outward convex to flush, and external force is needed, and the latter stage is a stage from flush to inward concave, and the stage can be automatically completed under the action of stress, and external force is not needed, so that negative rigidity is generated, and energy is saved; the concave curved beam has the same principle and the opposite direction to the convex curved beam, and also has the advantage of larger expansion ratio; in the barrel wall deflection process, the energy-saving effect can be achieved as long as one hollow reaches the later stage.
The invention has the beneficial effects that: compared with the existing positive stiffness supporting structure, the invention has the advantages of small driving force requirement and less energy consumption under the condition of larger deflection angle. The invention has certain bending rigidity and can bear the aerodynamic load of the deflection head rocket in the flying process, thereby maintaining the aerodynamic appearance of the deflection head rocket. The invention designs different supporting structures by matching two basic configurations of the outer convex curved beam and the inner concave curved beam, and has flexible and various applications.
Description of the drawings:
FIG. 1 is a schematic view of a top beam or a bottom beam which is arranged in a triangular shape and is retained around each hollow part of a cylinder wall and is a convex curved beam;
FIG. 2 is a schematic view of a top beam or a bottom beam which is arranged in a triangular shape and is arranged around each hollow part of the cylinder wall and is concave;
FIG. 3 is a schematic diagram of a barrel wall comprising both outwardly convex and inwardly concave curved beam hollowed-out sections, and arranged in an ABBA manner;
FIG. 4 is a schematic view of a previous stage of an inward deformation process of a convex curved beam under pressure;
FIG. 5 is a schematic view of the outward convex curved beam being subjected to a stress force and automatically completing the inward deformation process in a later stage;
FIG. 6 is a schematic view of a deflection drive mechanism disposed within a three-dimensional negative stiffness elastomeric frame;
FIG. 7 is a schematic illustration of deflection of a three-dimensional negative stiffness resilient frame.
The specific implementation mode is as follows:
referring to fig. 1 to 7, a three-dimensional negative-stiffness elastic frame comprises a cylinder wall 2 provided with a plurality of hollows 1, wherein the hollows 1 are arranged in a delta shape, and the left and right directions of the delta shape are arranged along the circumferential direction of the cylinder wall 2; the cylinder can be a cylinder, an elliptic cylinder, a square cylinder, a polygonal cylinder and the like or a cylinder with any shape such as a straight cylinder, a bent cylinder, a reducer cylinder and the like, and can be arranged according to the head requirement of the aircraft; because the cylinder wall 2 is provided with the hollow parts 1 which are arranged in a delta shape and are arranged along the circumferential direction of the cylinder wall 2, the cylinder wall 2 can have the function of elastic deformation along the axial direction like a spring, thereby realizing integral deflection; the above is the prior art; the cylinder wall 2 retained around each hollow part 1 arranged in a shape like a Chinese character 'pin' comprises a top beam 2-1, a bottom beam 2-2 and vertical beams 2-3 at two sides, namely four beams enclosed into a shape like a Chinese character 'kou'; the top beam 2-1 and/or the bottom beam 2-2 which are/is retained around each hollow part 1 which is arranged in a shape like a Chinese character 'pin' are/is a convex or concave curved beam; the outward convex curved beam is divided into two stages by the inward deformation process under pressure, the former stage is a stage from outward convex to flush, and external force is needed, and the latter stage is a stage from flush to inward concave, and the stage can be automatically completed under the action of stress, and external force is not needed, so that negative rigidity is generated, and energy is saved; the concave curved beam has the same principle and the opposite direction to the convex curved beam, and also has the advantage of larger expansion ratio; in the deflection process of the cylinder wall 2, the energy-saving effect can be achieved as long as one hollow-out 1 reaches the later stage.
Under the condition that the top beam 2-1 and the bottom beam 2-2 retained around each hollow-out 1 arranged in a shape like a Chinese character 'pin' on the cylinder wall 2 are convex curved beams, when the cylinder wall 2 is independently compressed, the diameter of the cylinder wall 2 can be greatly changed, but the cylinder wall 2 can be bound by skins in actual use, and a better negative stiffness effect can also be realized; the principle that the top beam 2-1 and the bottom beam 2-2 are both concave curved beams is the same.
A deflection driving mechanism 3, such as a piezoelectric ceramic driving mechanism, a magnetostrictive driving mechanism, a hydraulic pump driving mechanism, a servo motor driving mechanism and the like, is arranged in the three-dimensional negative-stiffness elastic frame and used for controlling the deflection of the frame, so that the deflection control of the warhead can be realized.
In the first embodiment, the top beam 2-1 and/or the bottom beam 2-2 retained around each hollow part 1 of the cylinder wall 2 in the delta arrangement are/is a convex curved beam, and when the warhead needs to deflect upwards, the deflection driving mechanism 3 positioned on the upper side contracts to compress the upper side of the cylinder wall 2.
In the second embodiment, the top beam 2-1 and/or the bottom beam 2-2 retained around each hollow part 1 of the cylinder wall 2 in the delta-shaped arrangement are/is an inwards concave curved beam, and when the warhead needs to deflect upwards, the deflection driving mechanism 3 positioned on the lower side extends to enable the lower side of the cylinder wall 2 to extend.
In the third embodiment, the cylinder wall 2 not only comprises the convex curved beam hollow-out section 1, but also comprises the concave curved beam hollow-out section 1, so that the deflection driving control is more flexible. The convex curved beam hollow-out section 1 and the concave curved beam hollow-out section 1 can be flexibly matched according to needs, the convex curved beam hollow-out section 1 is set to be A, the concave curved beam hollow-out section 1 is set to be B, and the convex curved beam hollow-out section 1 and the concave curved beam hollow-out section 1 can be matched in any mode such as ABAB, ABBA and BAAB.
Preferably, the continuous curved beam has a cosine waveform, and the deformation and recovery are smooth.
The material of the cylinder wall 2 can be metal, such as aluminum alloy, steel, etc., or fiber, such as carbon fiber, graphene fiber, carbon nanotube fiber, etc., reinforced composite material.
Claims (5)
1. A three-dimensional negative-stiffness elastic frame comprises a cylinder wall (2) provided with a plurality of hollows (1), wherein the hollows (1) are arranged in a delta shape, and the left and right directions of the delta shape are arranged along the circumferential direction of the cylinder wall (2); the triangular hollow beam is characterized in that the barrel wall (2) reserved around each hollow (1) distributed in a triangular shape comprises a top beam (2-1), a bottom beam (2-2) and vertical beams (2-3) on two sides, and the top beam (2-1) and/or the bottom beam (2-2) reserved around each hollow (1) distributed in a triangular shape are convex or concave curved beams.
2. The three-dimensional elastic frame with negative rigidity according to claim 1, characterized in that the top beam (2-1) and/or the bottom beam (2-2) retained around each hollow (1) of the triangular arrangement of the cylinder wall (2) are/is an outward convex curved beam.
3. The three-dimensional elastic frame with negative rigidity according to claim 1, characterized in that the top beam (2-1) and/or the bottom beam (2-2) retained around each hollow (1) of the triangular arrangement of the cylinder wall (2) are/is an inwards concave curved beam.
4. The three-dimensional elastic frame with negative rigidity according to claim 1, wherein the cylinder wall (2) comprises both the convex curved beam hollow (1) section and the concave curved beam hollow (1) section.
5. The three-dimensional negative stiffness elastomeric frame of claim 1, 2, 3 or 4, wherein the continuous curved beam has a cosine wave shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111472286.XA CN114111461A (en) | 2021-12-03 | 2021-12-03 | Three-dimensional negative-stiffness elastic frame |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111472286.XA CN114111461A (en) | 2021-12-03 | 2021-12-03 | Three-dimensional negative-stiffness elastic frame |
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| Publication Number | Publication Date |
|---|---|
| CN114111461A true CN114111461A (en) | 2022-03-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111472286.XA Pending CN114111461A (en) | 2021-12-03 | 2021-12-03 | Three-dimensional negative-stiffness elastic frame |
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| Country | Link |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116211254A (en) * | 2023-03-09 | 2023-06-06 | 华中科技大学同济医学院附属同济医院 | Device and method for acquiring hardness parameters of target object |
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| CN102700704A (en) * | 2012-05-30 | 2012-10-03 | 南京航空航天大学 | Deformation skin for aircraft |
| CN103105103A (en) * | 2012-12-21 | 2013-05-15 | 哈尔滨工业大学 | Ammunition with head capable of deflecting and based on smart material driver |
| US20160032997A1 (en) * | 2014-08-01 | 2016-02-04 | Board Of Regents, The University Of Texas System | Negative stiffness honeycomb material |
| WO2018189719A1 (en) * | 2017-04-13 | 2018-10-18 | Lead Tech S.R.L. | Multistable, compressible, composite metamaterial with articulated elements and which can be made with 3d printing processes |
| CN110371324A (en) * | 2019-07-22 | 2019-10-25 | 哈尔滨工业大学 | A kind of solar sail being unfolded by multistable curved beam intelligent drives |
| CN110375050A (en) * | 2019-07-22 | 2019-10-25 | 哈尔滨工业大学 | A kind of new spatial Intelligent telescopic transport structure based on multistable curved beam |
| CN111678386A (en) * | 2020-07-03 | 2020-09-18 | 南京航空航天大学 | Aircraft head deflection control device |
| CN113267092A (en) * | 2021-06-02 | 2021-08-17 | 哈尔滨工业大学 | Deflection warhead deformation skin structure |
| CN113586660A (en) * | 2021-08-12 | 2021-11-02 | 重庆大学 | Modularized quasi-zero rigidity vibration isolation structure |
-
2021
- 2021-12-03 CN CN202111472286.XA patent/CN114111461A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102700704A (en) * | 2012-05-30 | 2012-10-03 | 南京航空航天大学 | Deformation skin for aircraft |
| CN103105103A (en) * | 2012-12-21 | 2013-05-15 | 哈尔滨工业大学 | Ammunition with head capable of deflecting and based on smart material driver |
| US20160032997A1 (en) * | 2014-08-01 | 2016-02-04 | Board Of Regents, The University Of Texas System | Negative stiffness honeycomb material |
| WO2018189719A1 (en) * | 2017-04-13 | 2018-10-18 | Lead Tech S.R.L. | Multistable, compressible, composite metamaterial with articulated elements and which can be made with 3d printing processes |
| CN110371324A (en) * | 2019-07-22 | 2019-10-25 | 哈尔滨工业大学 | A kind of solar sail being unfolded by multistable curved beam intelligent drives |
| CN110375050A (en) * | 2019-07-22 | 2019-10-25 | 哈尔滨工业大学 | A kind of new spatial Intelligent telescopic transport structure based on multistable curved beam |
| CN111678386A (en) * | 2020-07-03 | 2020-09-18 | 南京航空航天大学 | Aircraft head deflection control device |
| CN113267092A (en) * | 2021-06-02 | 2021-08-17 | 哈尔滨工业大学 | Deflection warhead deformation skin structure |
| CN113586660A (en) * | 2021-08-12 | 2021-11-02 | 重庆大学 | Modularized quasi-zero rigidity vibration isolation structure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116211254A (en) * | 2023-03-09 | 2023-06-06 | 华中科技大学同济医学院附属同济医院 | Device and method for acquiring hardness parameters of target object |
| CN116211254B (en) * | 2023-03-09 | 2023-09-05 | 华中科技大学同济医学院附属同济医院 | Device and method for acquiring hardness parameters of target object |
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Application publication date: 20220301 |
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