CN105836164A - Interstage adaptive structure of spacecraft - Google Patents

Abstract

The invention relates to an adaptive structure, in particular to an interstage adaptive structure of a spacecraft. The interstage adaptive structure of the spacecraft comprises an upper end frame (1), a lower end frame (2), a supporting beam (5), an upper connector (3) and a lower connector (4). The supporting beam (5) is composed of one or more buckling beams (7), axial loads are applied to the buckling beam (7), the forked position of the buckling beam is subjected to bending deflection, and when the loads are close to critical buckling loads, a connecting screw (8), a negative-stiffness metal reed (9), a damping gasket (10) and a linear spring (12) are mounted at the transverse deformation position of the Euler's buckling beam (7). The interstage adaptive structure has the advantages of being high in longitudinal stiffness and large in transverse damping output, the requirement of the structure for high stiffness connection is met, the need for vibration reduction and isolation can be met through large transverse damping output, and the problem that the high stiffness and high damping of a traditional structure contradict each other and are incompatible is solved.

Description

A kind of spacecraft inter-stage adapter structure

Technical field

The present invention relates to a kind of adapter structure, be specifically related to a kind of spacecraft inter-stage adapter structure.

Background technology

It is the highest that the elastic modelling quantity of usual material and fissipation factor present contrary variation tendency, i.e. elastic modelling quantity, and fissipation factor is more Little.Therefore, above material is utilized also to show corresponding variation characteristic, i.e. structure as carrying its rigidity of structure and damping firm Spend the highest, damping vibration attenuation effect is the poorest.

Typical spacecraft inter-stage adapter structure includes satellite-rocket docking structure, the cabin section connection structure of star ship, special installation load With the attachment structure etc. of star ship, inter-stage adapter structure needs possess good rigidity, to ensure being reliably connected of spacecraft inter-stage, Also there is good damping vibration attenuation characteristic, with the performance indications of improving product.

Domestic and international existing spacecraft inter-stage adapter structure, mainly based on truss structure or semi-monocoque construction, has good company Connect rigidity, but it is poor to subtract anti-vibration performance.

Summary of the invention

It is an object of the invention to: for solving conventional aerospace device inter-stage adapter structure high rigidity, high-damping is conflicting, can not be total to The problem deposited, it is provided that a kind of have longitudinally high rigidity, the feature of the biggest damping output, had both met what structure high rigidity connected Requirement, can realize subtracting the spacecraft inter-stage adapter structure of vibration isolation demand by the biggest damping output again.

The technical scheme is that a kind of spacecraft inter-stage adapter structure, it includes: upper end frame, lower end frame, is used for supporting Upper end frame, the support beam of lower end frame, the two ends of support beam are connected with upper end frame, lower end frame by top connection, lower contact respectively；

Support beam includes: one or more buckled beam, buckled beam is applied axial load P so that it is send out in bifurcation Raw flexural deformation, when buckled beam midway deflection reaches to set q, at the vertically-mounted connection in the transversely deforming position screw rod of buckled beam, Connect the two ends of screw rod symmetrical be socketed with negative stiffness metal spring leaf, metal spring leaf is compressed on connection screw rod by hold-down bolt head, The both sides of metal spring leaf are provided with damping gasket；Damping gasket realizes fixing by the pressing plate inside attachment screw and buckled beam； It is provided with Hookean spring between two block pressur plates inside buckled beam.

Beneficial effect: a kind of spacecraft inter-stage adapter structure with high rigidity high-damping whole characteristic that (1) is involved in the present invention, tool There are longitudinally high rigidity, the feature of the biggest damping output, both met the requirement that structure high rigidity connects, again can be by the biggest resistance Buddhist nun exports realization and subtracts vibration isolation demand, solves traditional structure high rigidity, high-damping problem conflicting, incompatible.For Satellite-rocket docking structure, loading device mounting structure etc., on the basis of ensureing higher coupling stiffness, it is possible to achieve subtract vibration isolation, it is possible to It is effectively isolated the mal-condition of vehicle, on the one hand reduces the design difficulty of satellite or loading device, on the other hand bigger lifting The performance indications of Space Vehicle System.

(2) a kind of spacecraft inter-stage adapter structure with high rigidity high-damping whole characteristic involved in the present invention, its core component is High rigidity support beam, the buckled beam of support beam, Hookean spring, negative stiffness metal spring leaf, high-damping pad be can design element, By regulating the design parameter of each element, inter-stage adapter structure stiffness characteristics can be realized, subtract the optimization of anti-vibration performance and dynamic characteristic.

Accompanying drawing explanation

Fig. 1 is the structural representation of the present invention；

Fig. 2 is the structural representation of support beam in the present invention；

Fig. 3 is the structural representation of buckled beam in the present invention；

Fig. 4 be in the present invention buckled beam by the schematic diagram of load displacement.

Detailed description of the invention

Seeing accompanying drawing 1, a kind of spacecraft inter-stage adapter structure, it includes: upper end frame 1, lower end frame 2, is used for supporting upper end frame 1, the support beam 5 of lower end frame 2, the two ends of support beam 5 are connected upper end frame 1, lower end by top connection 3 with lower contact 4 respectively Frame 2；

Seeing accompanying drawing 2,3, support beam 5 is made up of one or more buckled beam 7, and support beam 5 is added by metal material machine Or carbon fibre composite one curing molding, buckled beam 7 is applied axial load so that it is occur bending and deformation in bifurcation, During near critical buckling load waiting, install in the transversely deforming position of buckled beam 7 and connect screw rod 8, connect the two ends pair of screw rod 8 Claim is socketed with negative stiffness metal spring leaf 9, and metal spring leaf 9 is fixed on connection screw rod 8 by hold-down bolt head 13, at medal spring The both sides of sheet 9 are provided with damping gasket 10；Damping gasket 10 is by the pressing plate 11 inside attachment screw 14 and buckled beam 7 Realize fixing；It is provided with Hookean spring 12 between two block pressur plates 11 inside buckled beam 7.

To buckled beam 7 as the carrying structure of a quasi-representative, when its axially institute loaded close to Critical Buckling Load time performance shaft Big to load-bearing rigidity, the less even negative unique mechanical feature of lateral stiffness, transversely series connection Hookean spring 12, damping gasket 10 and negative stiffness metal spring leaf 9 realize damping unit large deformation；Meanwhile, in order to ensure that horizontal dynamic stability utilizes buckled beam horizontal Equivalent stiffness to rigidity with Hookean spring and negative stiffness metal spring leaf 9 matches.

By changing the initial tilt of buckled beam 7, adjustable lateral stiffness and the size of longitudinal rigidity, it addition, Hookean spring 12, Damping gasket 10 and negative stiffness metal spring leaf 9 be also can design element, by regulate each element design parameter, level can be changed Between adapter structure rigidity, damping output.Therefore, when designing inter-stage adapter structure, can be according to higher level's spacecraft (or load Equipment) rigidity, damping requirements, adapter structure is designed targetedly.

See accompanying drawing 4, in an initial condition, single middle initial deflection q of buckled beam 7₀, under the effect of vertical load P, Its end vertical deviation is y, and midway deflection is q；

$P=P_e\[1-\mathrm{\π}\left(\frac{q_0}{L}\right){({\mathrm{\π}}^2{\left(\frac{q_0}{L}\right)}^2+4(\frac{y}{L}\left)\right)}^{-1/2}\]\[1+\frac{{\mathrm{\π}}^2}{8}{\left(\frac{q_0}{L}\right)}^2+\frac{1}{2}\left(\frac{y}{L}\right)\]$

Wherein, P_e=EI (π/L)², L be buckled beam 7 not deformed time length, E is elasticity modulus of materials, I be curved beam cross section be used to Property square.

Between adapter structure involved in the present invention and higher level's spacecraft, both can connect by screw is fixing, it is also possible to pass through firer Lock realizes connecting and separating in-orbit.

It is provided with through hole, as inter-stage adapter structure and lower end spacecraft on inter-stage adapter structure lower end frame 2 involved in the present invention Fixing connection interface.

For satellite and the rocket adapter structure, the star cabin section connection structure that has separation demand, lock type of attachment by firer, it is possible to achieve The separation in-orbit of two-stage spacecraft；For loading device, without separating the star cabin section connection structure of demand, realized solid by screw Fixed connection.

Claims (3)

1. a spacecraft inter-stage adapter structure, it includes: upper end frame (1), lower end frame (2), is used for supporting described Upper end frame (1), the support beam (5) of lower end frame (2), the two ends of described support beam (5) are respectively by upper Joint (3) is connected with described upper end frame (1), described lower end frame (2) with lower contact (4), and its feature exists In:

Described support beam (5) including: one or more buckled beam (7), executes described buckled beam (7) Add axial load P so that it is occur bending and deformation in bifurcation, treat that buckled beam (7) midway deflection reaches to set When determining q, in the vertically-mounted connection in transversely deforming position screw rod (8) of described buckled beam (7), described connection What the two ends of screw rod (8) were symmetrical is socketed with negative stiffness metal spring leaf (9), and described metal spring leaf (9) is by pressing Tight bolt head (13) is compressed on described connection screw rod (8), sets in the both sides of described metal spring leaf (9) It is equipped with damping gasket (10)；Described damping gasket (10) passes through attachment screw (14) and described buckled beam (7) pressing plate (11) of inner side realizes fixing；Two pieces of described pressing plates (11) in described buckled beam (7) inner side Between be provided with Hookean spring (12).

2. a kind of spacecraft inter-stage adapter structure as claimed in claim 1, it is characterised in that in an initial condition, Initial deflection q in the middle of single buckled beam (7)₀, under the effect of axial load P, its end vertical deviation is Y, midway deflection is q；

$P=P_e\[1-\mathrm{\π}\left(\frac{q_0}{L}\right){\left({\mathrm{\π}}^2{\left(\frac{q_0}{L}\right)}^2+4\left(\frac{y}{L}\right)\right)}^{-1/2}\]\[1+\frac{{\mathrm{\π}}^2}{8}{\left(\frac{q_0}{L}\right)}^2+\frac{1}{2}\left(\frac{y}{L}\right)\]$

Wherein, P_e=EI (π/L)², L be buckled beam (7) not deformed time length, E is elasticity modulus of materials, and I is bent Beam section the moment of inertia.

3. a kind of spacecraft inter-stage adapter structure as claimed in claim 1 or 2, it is characterised in that described support Beam (5) is added by metal material machine or carbon fibre composite one curing molding.