CN115863955A - Deployable antenna for micro-nano satellite - Google Patents
Deployable antenna for micro-nano satellite Download PDFInfo
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- CN115863955A CN115863955A CN202211672492.XA CN202211672492A CN115863955A CN 115863955 A CN115863955 A CN 115863955A CN 202211672492 A CN202211672492 A CN 202211672492A CN 115863955 A CN115863955 A CN 115863955A
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Abstract
The invention provides a deployable antenna feed source for a micro-nano satellite, which comprises a base, a deployable reflecting surface, a support rod and a feed source, wherein the deployable reflecting surface is fixed on the base and used for receiving a feed source signal, the deployable reflecting surface is fixed on the base and used for receiving the feed source signal, the support rod is erected in the center of the deployable reflecting surface, the support rod is connected with a feed source capable of emitting a radio frequency signal, the feed source comprises a spiral line radiator, a spiral line support frame, a ground plane and a wave guide plate, and the radiation mode of the feed source is a back radiation mode. The device provided by the invention has a simple structure and is convenient to install, and the transmission rate of data transmission communication can be effectively improved.
Description
Technical Field
The invention belongs to the field of aerospace signal transmission, and particularly relates to an expandable antenna for a micro-nano satellite.
Background
Due to the characteristic of small size of the microsatellite, the size of the data transmission communication antenna is limited, the radiation gain of the antenna is influenced, the transmission rate of a data transmission communication system is further influenced, in order to increase the transmission rate of the data transmission communication system, the data transmission antenna is designed into an expandable structure, the data transmission antenna is expanded after the satellite is in orbit, the aperture of a reflecting surface of the antenna is increased, and therefore the antenna gain and the transmission rate of the data transmission communication system are improved.
However, most of the prior art uses a bidirectional feed source or a forward feed source, which either reduces the electrical radiation performance of the antenna or requires a receiving device with an excessively large volume and is not suitable for being arranged on the micro-nano satellite.
Patent document CN115508997A discloses an extra-large aperture space telescope and its expansion mode, in which an optical reflection surface lens is divided into a plurality of solid panels with the same shape, and an independent optical reflection surface back supporting truss is arranged on the back surface of each solid panel. In the unfolding stage, the rotary mechanism is driven, the back supporting trusses of the optical reflecting surfaces are opened along the radial direction and are simultaneously twisted, and the plurality of solid panels with the same shape are driven to be opened by taking the hub as the center and perform twisting action, so that the central optical telescope is unfolded. After the optical telescope is unfolded in place, the cell star is adopted to stretch outwards to realize radial stretching of the extensible truss, and the microwave reflecting surface connected with the extensible truss is driven to be unfolded together to form the microwave telescope. The reflecting surface which needs to be unfolded is very large, and the device is not suitable for micro-nano satellites.
Patent document CN217691657U discloses a low earth orbit satellite terminal antenna, comprising: the square flat plate feed source is fixed at a position corresponding to a focal point of the reflecting surface, and the square flat plate feed source is matched with a wave beam of the reflecting surface. The antenna adopts the conventional forward feed head design, and a forward feed head support needs to be additionally arranged, so that the volume of the whole terminal antenna is too large and cannot be further reduced.
Patent document CN103579769A discloses a small X-band circularly polarized feed source, which comprises a cylindrical cavity with a small opening angle circular horn, a spiral line, a medium support and a high-frequency coaxial socket. The device only considers reducing the volume of the feed source head, thereby meeting the requirement of device miniaturization, but when the feed source head is reduced, the emission signal quantity is reduced at the same time, and the final information transmission efficiency is reduced.
Disclosure of Invention
In order to solve the problems, the invention provides the deployable antenna for the micro/nano satellite, and the deployable antenna has a simple structure and is convenient to install, and the transmission rate of data transmission communication can be effectively improved.
The utility model provides an expandable antenna for receiving satellite a little, includes the base, fixes on the base, is used for receiving the expandable plane of feed signal, erects the bracing piece at expandable plane center, has connected the feed that can launch radio frequency signal on the bracing piece, the feed includes helix irradiator, helix support frame, ground plane and guided wave board, the radiation pattern of feed is the radiation pattern that faces back.
The invention realizes the reverse radiation of the feed source signal by the spiral line radiator, the grounding plate and the wave guide plate which are sequentially arranged on the same feed source, and simultaneously receives the feed source signal transmitted by the feed source head by the expanding reflecting surface, thereby effectively increasing the radiation gain of the expandable data transmission antenna and improving the transmission rate of data transmission communication.
Specifically, the antenna signal is an X-band circularly polarized radio frequency signal.
Specifically, the diameter of the grounding plate is 0.3 lambda, wherein lambda represents the wavelength of the radio frequency signal of the antenna.
Specifically, the number of the wave guide plates is three along the axial direction of the feed source support frame, the distance between every two wave guide plates is 1/4 lambda, and lambda represents the wavelength of an antenna radio-frequency signal.
Specifically, the diameter of the wave guide plate is 0.3 λ, where λ represents the wavelength of the antenna radio frequency signal.
Preferably, the deployable reflecting surface is made of gold-plated molybdenum materials, so that the flexibility of the deployable reflecting surface can be ensured, and signal energy cannot be lost in the transmitting process.
Preferably, the size of the mesh of the expandable reflection is less than 0.1 λ, wherein λ represents the wavelength of the antenna radio frequency signal; when the mesh is too large, there is a problem that signal energy is easily lost, and when there is no mesh, there is a problem that the material is excessively used and the cost is excessively high.
Preferably, the support rod further comprises a telescopic mechanism for changing the relative distance between the feed source and the expandable emission surface, and the distance between the feed source and the expandable emission surface can be changed to lift the radiation phase center of the feed source to the section focus formed by the reflection surface, so that the signal emission effect is maximized.
Compared with the prior art, the invention has the beneficial effects that:
the invention designs the X-band deployable reflector antenna feed source which has a simple structure, is convenient to install with the deployable reflector, can adapt to high and low temperature environments, can effectively increase the radiation gain of the deployable data transmission antenna and improve the transmission rate of a data transmission communication system.
Drawings
Fig. 1 is a schematic view illustrating a folded state of an expandable antenna according to the present invention;
fig. 2 is a schematic view of an unfolded state of the deployable antenna provided by the present invention;
FIG. 3 is a schematic structural diagram of a feed source provided by the present invention;
FIG. 4 is a cross-sectional cut-away view of a feed provided by the present invention;
FIG. 5 is a cross-sectional view of a support bar provided by the present invention;
FIG. 6 is a signal radiation pattern of a feed source provided by the present invention;
fig. 7 is a standing wave diagram of a feed provided by the present invention.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In one embodiment, the center frequency wavelength λ of the antenna RF signal has a value of 36.6mm.
As shown in fig. 1 and fig. 2, the deployable antenna includes a base 4, a deployable reflecting surface 3 fixed on the base 4 for receiving a signal of a feed source, a supporting rod 2 erected at the center of the deployable reflecting surface 3, and the feed source 1 capable of transmitting the signal is connected to the supporting rod 2.
The deployable reflecting surface 3 is made of gold-plated molybdenum material, so that the flexibility of the deployable reflecting surface can be ensured, signal energy cannot be lost in the reflecting process, and the mesh size of the deployable reflecting surface is less than 0.1 lambda (2 mm in the embodiment); when the mesh is too large, there is a problem that signal energy is easily lost, and when there is no mesh, there is a problem that the material is excessively used and the cost is excessively high.
When the extensible reflecting surface 3 is folded, the size of the whole device can be greatly reduced, so that the launching cabin which originally can only contain one micro-nano satellite can contain two or even a plurality of micro-nano satellites.
When the extensible reflecting surface 3 is unfolded, the extensible reflecting surface and the extended feed source form a parabolic reflecting surface antenna, so that normal signal transmission work of the micro-nano satellite is met.
As shown in fig. 3, it is a structure diagram of the feed source. The spiral line radiator 1-1 is used for radiating X-band circularly polarized radio frequency signals, and the spiral line support frame 1-2 is used for fixing the spiral line radiator 1-1.
The ground plane 1-3 is used for connecting the spiral line support frame 1-2 and is used as the ground plane of the spiral radiator 1-1, and in addition, the diameter of the ground plate of the embodiment is 10.98 mm.
The three wave guide plates 1-4 are arranged below the ground plane 1-3 at equal intervals, the distance between every two wave guide plates 1-4 is 1/4 lambda, and the diameter of each wave guide plate is 10.98mm, so that X-band circularly polarized radio frequency signals emitted by the spiral line radiator 1-1 can be guided to be radiated reversely to the deployable reflecting surface 3.
And the feed source 1 also comprises a support frame 1-5 used for connecting the grounding plate 1-3 and the feed source fixing base 1-6, the feed source fixing base 1-6 fixedly connected with the support rod 2, and an SMA joint 1-7 used for connecting an external cable for feeding.
As shown in fig. 4, the cross-sectional view of the feed source 1 is a cross-sectional view of the support frame 1-5 and the spiral support frame 1-2, which are hollow and communicated, and the end of the spiral radiator 1-1 is fixed at a fixed point 1-9 of the spiral support frame 1-2, then wound on the surface of the spiral support frame 1-2, and then wired from the inside to pass through the support frame 1-5 and connected to the SMA connector 1-7 at the bottom, so that the spiral radiator 1-1 is not affected by the external environment, and the use effect of the spiral radiator 1-1 is prevented from being affected by the high temperature possibly existing when the satellite is sent to a target position.
As shown in fig. 5, which is a cross-sectional view of the support rod 4, the upper sleeve 4-1 can be extended and retracted relative to the lower sleeve 4-2, and the height of the feed source 1 can be adjusted by the telescopic structure, so that the radiation phase center of the feed source 1 is lifted to the section focus formed by the reflecting surface, thereby maximizing the signal transmission effect.
As shown in fig. 6, it is obvious from the figure that the deployable antenna feed is in a back radiation mode, and when the radiation phase center of the feed 1 extends to the cross-sectional focus formed by the reflecting surface, the final radiation energy can irradiate the whole deployable reflecting surface 5, thereby increasing the radiation gain of the deployable antenna.
As shown in fig. 7, a standing wave diagram of the deployable antenna feed is shown, the standing wave of the antenna is generally required to be less than 2, and the standing wave of the antenna is less than 1.5 in a required frequency band, so that it is obvious that the deployable antenna feed has good impedance matching.
Claims (8)
1. The utility model provides an expandable antenna for receiving satellite a little, its characterized in that includes the base, fixes on the base, is used for receiving the expandable plane of reflection of feed signal, erects the bracing piece at expandable plane of reflection center, has connected the feed that can launch radio frequency signal on the bracing piece, the feed includes helix irradiator, helix support frame, ground plane and guided wave board, the radiation pattern of feed is the dorsad radiation pattern.
2. A deployable antenna for a micro-nano satellite according to claim 1, wherein the antenna signals are X-band circularly polarized radio frequency signals.
3. A deployable antenna for micro-nano satellites according to claim 1, wherein the diameter of the ground plane is 0.3 λ, where λ represents the wavelength of an antenna radio frequency signal.
4. The deployable antenna for a micro-nano satellite according to claim 1, wherein the number of the wave guide plates is three along the axis direction of the feed support frame, and the distance between every two wave guide plates is 1/4 lambda.
5. A deployable antenna for micro-nano satellites according to claim 1 or 4, wherein the diameter of the wave guide plate is 0.3 λ, and λ represents the wavelength of the radio frequency signal of the antenna.
6. The deployable antenna for a micro-nano satellite according to claim 1, wherein the deployable reflecting surface is made of gold-plated molybdenum material.
7. A deployable antenna for micro-nano satellites according to claim 1 or 6, wherein the mesh size of the deployable reflection is less than 0.1 λ, where λ represents the wavelength of the antenna radio frequency signal.
8. The deployable antenna for a micro-nano satellite according to claim 1, wherein the support rod further comprises a telescoping mechanism for changing the relative distance between the feed source and the deployable reflecting surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211672492.XA CN115863955A (en) | 2022-12-26 | 2022-12-26 | Deployable antenna for micro-nano satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211672492.XA CN115863955A (en) | 2022-12-26 | 2022-12-26 | Deployable antenna for micro-nano satellite |
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| Publication Number | Publication Date |
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| CN115863955A true CN115863955A (en) | 2023-03-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202211672492.XA Pending CN115863955A (en) | 2022-12-26 | 2022-12-26 | Deployable antenna for micro-nano satellite |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116387793A (en) * | 2023-05-29 | 2023-07-04 | 四川省安道速博科技有限公司 | ADS-B signal receiving and transmitting equipment for aviation application |
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2022
- 2022-12-26 CN CN202211672492.XA patent/CN115863955A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116387793A (en) * | 2023-05-29 | 2023-07-04 | 四川省安道速博科技有限公司 | ADS-B signal receiving and transmitting equipment for aviation application |
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