Integrated structure of rigidized inflatable deployable truss type planar antenna and solar array

Abstract

The invention provides an integrated structure of a rigidized inflatable deployable truss type planar antenna and a solar array. A substrate of the solar array provided by the invention is arranged at the upper side of a truss structure; a solar cell slice is fixed on the upper surface of the solar array; a planar antenna module is arranged at the lower side of the truss structure to form the planar antenna; and a satellite or a space station is arranged at the middle part or the end part of the truss structure. In the invention, a rigidized inflatable deployable truss is used as the main body of the integrated structure; the truss can be flexibly folded during launching, is high in folding efficiency, small in launching volume and convenient for the traditional launching technology and launching equipment to launch large-aperture antennae and large-area solar arrays; after the launched large-aperture antennae and large-area solar arrays enter tracks, the integrated structure is unfolded and rigidized, is higher in structural rigidity and fundamental vibrational frequency and is beneficial to the posture control and the stable running on tracks of aircrafts such as the satellite and the like, the remarkable improvement of anti-vibration performance of the planar antenna and the improvement of precision and sensitivity of signals.

Description

technical field [0001] The invention relates to an integrated structure of a truss-type planar antenna and a solar sail panel that can be rigidized and inflated. Background technique [0002] Planar antennas and solar panels (solar arrays or solar wings) have been widely used in satellites, manned spacecraft, space stations and other aircraft. Planar antennas are used for spaceborne synthetic aperture radar as signal transceiver components, and solar panels are used Space vehicles such as satellites are used as power supply components, but the planar antennas or solar panels used in the current aircraft are all in the form of mechanical unfolded structures, and are installed separately on the aircraft. [0003] Existing deployable solar panels mainly adopt a mechanical unfolding support structure, which is composed of many rigid components connected through a connecting mechanism, a control unfolding mechanism and a locking mechanism, which has complex structures and is pron...

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Problems solved by technology

[0006] The purpose of the present invention is to solve the problem of complex structure, easy failure, poor deployment reliability, heavy overall weight, low folding efficiency, and poor emission of existing mechanical unfolded solar panels and existing mechanical unfolded planar antennas in single use. The problem of large volume and high cost; at the same time, it solves the problem that the structural stiffness and fundamental frequency decrease with the increase of the structure size due to the large-area planar frame type expansion structure, which is easy to cause resonance with the main body of the aircraft and makes it difficult to control the attitude of the aircraft, and leads to The problem of the decrease in signal accuracy of planar antennas, and then provide a rigid inflatable unfolding truss-type planar antenna and solar panel integrated mechanism

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