Air-drop throwing type terminal

Abstract

The utility model relates to an air-drop throwing type terminal. The air-drop throwing type terminal comprises a shell; the maximum gain radiation direction of the first antenna points to the upper surface of the terminal; the maximum gain radiation direction of the second antenna points to the lower surface of the terminal; a gravity detection sensor; the input end of the CPU control unit is electrically connected with the gravity detection sensor, the output end of the CPU control unit is electrically connected with a radio frequency wireless transceiver and a radio frequency matching circuit in sequence, and the control end of the CPU control unit is electrically connected with the control end of the single-pole double-throw switch; the input end of the single-pole double-throw switch is electrically connected with the radio frequency matching circuit, and the output end of the single-pole double-throw switch is electrically connected with the first antenna and the second antenna respectively; the gravity detection sensor detects the angle state between the terminal and the ground plane, and the CPU control unit controls the single-pole double-throw switch to be switched to the first antenna or the second antenna to work. Thus, through a unique structural design and an antenna switching mechanism, a good communication effect with a satellite can be ensured no matter how the terminal lands.

Description

Technical Field

[0001] The present application relates to the field of satellite communication technology, and in particular to an airdrop-type terminal. Background Art

[0002] In the field of satellite communication ground terminals, some terminals are difficult to install manually due to environmental factors. Instead, they must be dropped directly from aircraft onto the ground or ocean. These terminals require not only excellent concealment but also minimal size for portability and deployment. Furthermore, satellite communication terminals typically require high antenna directivity, aiming for maximum radiation to point skyward for optimal communication with the satellite.

[0003] like Figure 1 As shown in the figure, the traditional spray-type terminal mainly uses a ceramic antenna, which is fixed to the upper surface of the terminal, and its maximum radiation direction is also directed towards the upper surface of the terminal. Although this design meets the requirements of miniaturization to a certain extent, the posture of the terminal after landing is unpredictable, especially when the upper surface of the terminal is facing the ground, the maximum radiation direction of the antenna will not be facing the sky, which seriously affects the communication effect with the satellite. In addition, since the antenna size is relatively small due to the size of the terminal, this further increases the difficulty of antenna design, especially when the receiving frequency of the Tianqi low-orbit satellite constellation is in the UHF band. Because the wavelength of this band is long, traditional antenna solutions are often large in size and difficult to adapt to the needs of miniaturized terminals.

[0004] In summary, existing spray-and-drop terminal antenna solutions have many shortcomings in practical applications, particularly in terms of antenna directivity and terminal miniaturization. Therefore, a new design solution is urgently needed to overcome these shortcomings and ensure that spray-and-drop terminals can maintain good communication with satellites in any landing posture. Utility Model Content

[0005] In view of the above problems with the existing technology, this application provides an airdrop-type terminal that solves the problem that traditional airdrop-type terminals may not ensure that the antenna's maximum radiation direction is pointing skyward after landing, thereby affecting communication with satellites. Through a unique structural design and antenna switching mechanism, this application ensures that regardless of how the terminal lands, it can maintain good communication with the satellite.

[0006] To achieve the above objectives, the present application provides, in a first aspect, an airdrop-type terminal, comprising:

[0007] A shell with two frustum bottom surfaces interlocked and hollow inside;

[0008] A mainboard is arranged in the middle of the housing;

[0009] A first antenna is provided above the mainboard, with its maximum gain radiation direction pointing toward the upper surface of the terminal;

[0010] A second antenna is provided below the mainboard, with its maximum gain radiation direction pointing toward the lower surface of the terminal;

[0011] A gravity detection sensor is provided on the main board;

[0012] A CPU control unit, whose input end is electrically connected to the gravity detection sensor, whose output end is electrically connected to a radio frequency wireless transceiver and a radio frequency matching circuit in sequence, and whose control end is electrically connected to a control end of a single-pole double-throw switch;

[0013] a single-pole double-throw switch, an input end of which is electrically connected to the radio frequency matching circuit, and an output end of which is electrically connected to the first antenna and the second antenna respectively;

[0014] The gravity detection sensor detects the angle between the terminal and the ground plane, and controls the single-pole double-throw switch to switch to the first antenna or the second antenna for operation through the CPU control unit.

[0015] In this way, this application adopts a dual-antenna design, combined with a gravity detection sensor to detect the terminal's posture in real time, and automatically switches to the first antenna or the second antenna pointing to the sky in the direction of maximum gain according to the detection results. Therefore, it can adapt to various unpredictable landing postures and ensure good communication with the satellite in any landing posture, thereby improving the stability and reliability of communication.

[0016] To achieve the above-mentioned purpose, the second aspect of the present application provides an airdrop-type terminal, comprising:

[0017] A shell with two frustum bottom surfaces interlocked and hollow inside;

[0018] A mainboard is arranged in the middle of the housing;

[0019] A first antenna is provided above the mainboard, with its maximum gain radiation direction pointing toward the upper surface of the terminal;

[0020] A second antenna is provided below the mainboard, with its maximum gain radiation direction pointing toward the lower surface of the terminal;

[0021] A photoelectric tilt detection switch is provided on the main board and is electrically connected to the control end of the single-pole double-throw switch;

[0022] A CPU control unit, which is electrically connected to a radio frequency wireless transceiver and a radio frequency matching circuit in sequence;

[0023] a single-pole double-throw switch, an input end of which is electrically connected to the radio frequency matching circuit, and an output end of which is electrically connected to the first antenna and the second antenna respectively;

[0024] The photoelectric tilt detection switch detects the angle between the terminal and the ground plane to output a high level or a low level, thereby controlling the single-pole double-throw switch to switch to the first antenna or the second antenna to work.

[0025] In this way, this application adopts a dual-antenna design, combined with a photoelectric tilt detection switch to detect the terminal's posture in real time, and automatically switches to the first antenna or the second antenna pointing to the sky in the direction of maximum gain according to the detection results. Therefore, it can adapt to various unpredictable landing postures and ensure good communication with the satellite in any landing posture, thereby improving the stability and reliability of communication.

[0026] In some embodiments, it further includes:

[0027] a first shielding cover, provided on the upper surface of the mainboard, for protecting components of the mainboard and forming a complete reference ground for the first antenna together with the ground layer of the mainboard;

[0028] The second shielding cover is arranged on the lower surface of the mainboard, and is used to protect the components of the mainboard, and together with the ground layer of the mainboard, forms a complete reference ground for the second antenna.

[0029] In some embodiments, it further includes:

[0030] a first ceramic substrate, disposed on the first shielding cover and configured to provide physical support for the first antenna;

[0031] The second ceramic substrate is disposed on the second shielding cover and is used to provide physical support for the second antenna.

[0032] In some embodiments, the first antenna is electroplated on a surface of the first ceramic substrate, and the second antenna is electroplated on a surface of the second ceramic substrate.

[0033] In some embodiments, the length of the first ceramic substrate is less than the length of the first shielding cover;

[0034] The length of the second ceramic substrate is smaller than the length of the second shielding cover.

[0035] In some embodiments, the first antenna and the second antenna are angle-cut circularly polarized antennas, and the angle-cut direction of the first antenna differs from the angle-cut direction of the second antenna by 180 degrees.

[0036] In some embodiments, the outer diameter of the housing is 200 mm, the inner diameter is 170 mm, and the thickness is 30 mm.

[0037] In some embodiments, the terminal is a vertically symmetrical structure centered on the mainboard.

[0038] In some embodiments, the first shielding cover and the second shielding cover are made of stainless steel. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 This is a schematic diagram of the structure of a traditional airdrop terminal;

[0040] Figure 2 This is a top-down cross-sectional view of an airdrop-type terminal provided by the present application;

[0041] Figure 3 It is a side sectional view of an airdrop-type terminal provided by the present application;

[0042] Figure 4 This is a top view of an airdrop terminal provided by the present application;

[0043] Figure 5 This is a side view of an airdrop terminal provided by the present application;

[0044] Figure 6 This is a schematic diagram of the electrical connection relationship between a gravity detection sensor, a CPU control unit, a radio frequency wireless transceiver, a radio frequency matching circuit, and a single-pole double-throw switch provided by the present application;

[0045] Figure 7 1 is a schematic diagram of the S(1,1) parameters of the first antenna provided in this application;

[0046] Figure 8 is the radiation pattern of the first antenna provided in this application;

[0047] Figure 9 This is a schematic diagram of the S(1,1) parameters of the second antenna provided by this application;

[0048] Figure 10 is the radiation pattern of the second antenna provided in this application;

[0049] Figure 11 This is a schematic diagram of the electrical connection relationship between the photoelectric tilt detection switch, CPU control unit, radio frequency wireless transceiver, radio frequency matching circuit and single-pole double-throw switch provided by this application;

[0050] It should be understood that the sizes and shapes of the blocks in the above structural diagrams are for reference only and should not constitute an exclusive interpretation of the embodiments of the present invention. The relative positions and inclusion relationships between the blocks presented in the structural diagrams are merely schematic representations of the structural relationships between the blocks and do not limit the physical connection methods of the embodiments of the present invention. DETAILED DESCRIPTION

[0051] The technical solution provided by this application is further described below with reference to the accompanying drawings and examples. It should be understood that the system structure and business scenarios provided in the examples of this application are mainly for illustrating possible implementation methods of the technical solution of this application and should not be interpreted as the sole limitation of the technical solution of this application. It is known to those skilled in the art that with the evolution of the system structure and the emergence of new business scenarios, the technical solution provided by this application is also applicable to similar technical problems.

[0052] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those generally understood by those skilled in the art of the technical field of this application. In the event of any inconsistency, the meaning described in this specification or the meaning derived from the content recorded in this specification shall prevail. In addition, the terms used herein are only for the purpose of describing the embodiments of the present application and are not intended to limit this application. In order to accurately narrate the technical contents in this application, and in order to accurately understand the present invention, the following explanation or definition is given to the terms used in this specification before describing the specific embodiments.

[0053] The embodiment of the present application provides an airdrop-type terminal, such as Figure 2 and Figure 3 As shown, the terminal is a vertically symmetrical structure centered on the mainboard 2, including:

[0054] A hollow housing 1 is formed by interlocking two frustum bottom surfaces;

[0055] The mainboard 2 is arranged in the middle of the housing 1;

[0056] The first antenna 3 is provided above the mainboard 2, with its maximum gain radiation direction pointing to the upper surface of the terminal;

[0057] The second antenna 4 is provided below the mainboard 2, with its maximum gain radiation direction pointing toward the lower surface of the terminal;

[0058] A gravity detection sensor is provided on the main board 2;

[0059] A CPU control unit, whose input end is electrically connected to the gravity detection sensor, whose output end is electrically connected to a radio frequency wireless transceiver and a radio frequency matching circuit in sequence, and whose control end is electrically connected to a control end of a single-pole double-throw switch;

[0060] a single-pole double-throw switch, whose input end is electrically connected to the radio frequency matching circuit, and whose output end is electrically connected to the first antenna 3 and the second antenna 4 respectively;

[0061] The gravity detection sensor detects the angle between the terminal and the ground plane, and controls the single-pole double-throw switch to switch to the first antenna 3 or the second antenna 4 for operation through the CPU control unit.

[0062] To clarify, the RF transceiver is used to transmit and receive wireless signals within the RF frequency band; the RF matching circuit is used to achieve impedance matching between the first antenna 3, the second antenna 4, and the RF transceiver. By optimizing impedance matching, reflected waves can be reduced, signal distortion can be avoided, and the received signal quality and transmitted signal strength can be improved.

[0063] It should be noted that if Figure 4 、 5 As shown, the terminal of this application is designed as a disc-shaped structure, that is, a thin cylindrical body with chamfered sides, forming a circular flying saucer shape that is symmetrical from top to bottom. This design ensures that when the terminal is dropped and lands, it will only rest on the ground on one of the upper or lower surfaces, rather than landing upright with the side angled arc structure.

[0064] In this way, the present application adopts a dual-antenna design, combined with a gravity detection sensor to detect the terminal's posture in real time, and automatically switches to the first antenna 3 or the second antenna 4 pointing to the sky in the direction of maximum gain according to the detection results. Therefore, it can adapt to various unpredictable landing postures, ensuring good communication with the satellite in any landing posture, thereby improving the stability and reliability of communication.

[0065] In some embodiments, the gravity detection sensor may be welded on the mainboard 2 and located inside the first shielding case 5 or the second shielding case 6 mentioned below.

[0066] In some embodiments, it further includes:

[0067] A first shielding cover 5 is provided on the upper surface of the mainboard 2 to protect the components of the mainboard 2 and to form a complete reference ground for the first antenna 3 together with the ground layer of the mainboard 2;

[0068] The second shielding cover 6 is provided on the lower surface of the mainboard 2 to protect the components of the mainboard 2 and to form a complete reference ground for the second antenna 4 together with the ground layer of the mainboard 2 .

[0069] Exemplarily, the first shielding cover 5 and the second shielding cover 6 can be welded on the mainboard 2 respectively.

[0070] In this way, the shielding cover (including the first shielding cover 5 and the second shielding cover 6) can effectively block external electromagnetic interference, protect the internal electronic components from external electromagnetic noise, and ensure the purity and stability of the signal. At the same time, the shielding cover can also prevent the electromagnetic signals generated internally from leaking into the external environment, avoiding interference with other devices.

[0071] Furthermore, for the first antenna 3, the first shielding cover 5 also serves as a reference ground for the first antenna 3, forming a complete reference ground together with the ground layer of the motherboard 2. Similarly, for the second antenna 4, the second shielding cover 6 also serves as a reference ground for the second antenna 4, forming a complete reference ground together with the ground layer of the motherboard 2. This arrangement helps improve the radiation efficiency and directivity of the first antenna 3 and the second antenna 4.

[0072] In some embodiments, the first shielding cover 5 and the second shielding cover 6 are made of stainless steel.

[0073] In this way, metal stainless steel has high mechanical strength and can withstand large external shocks and vibrations, protecting internal electronic components from damage; metal stainless steel also has good thermal conductivity, which can help internal electronic components dissipate heat.

[0074] In some embodiments, it further includes:

[0075] a first ceramic substrate 7 , disposed on the first shielding cover 5 , for providing physical support for the first antenna 3 ;

[0076] The second ceramic substrate 8 is disposed on the second shielding cover 6 and is used to provide physical support for the second antenna 4 .

[0077] In some embodiments, the first antenna 3 is electroplated on the surface of the first ceramic substrate 7 , and the second antenna 4 is electroplated on the surface of the second ceramic substrate 8 .

[0078] Illustratively, the surfaces of the first ceramic substrate 7 and the second ceramic substrate 8 are electroplated to form a metal layer (such as copper or silver) to form the first antenna 3 and the second antenna 4 .

[0079] The ceramic substrate provides stable physical support for the antenna, ensuring it maintains its proper shape and position in a variety of environments and conditions. The ceramic substrate's high rigidity reduces the impact of external vibrations on antenna performance, improving antenna stability.

[0080] In some embodiments, the length of the first ceramic substrate 7 is less than the length of the first shielding cover 5;

[0081] The length of the second ceramic substrate 8 is smaller than the length of the second shielding cover 6 .

[0082] Among them, the reasons for making the length of the ceramic substrate shorter than the length of the shield are as follows:

[0083] (1) If the length of the ceramic substrate is the same as that of the shield, the radiation characteristics of the antenna may change, affecting its performance. By appropriately shortening the length of the ceramic substrate, the resonant frequency and radiation direction of the antenna can be better controlled, ensuring its optimal performance within a specific frequency band.

[0084] (2) Longer ceramic substrates are more likely to break or deform when subjected to external impact, while shorter ceramic substrates can provide better mechanical stability and reduce the risk of damage during transportation and use.

[0085] (3) A shorter ceramic substrate can reduce the overall weight and volume, which is particularly important for airdrop terminals because lightweighting and miniaturization can improve the portability and delivery accuracy of the terminal.

[0086] (4) Longer ceramic substrates will increase manufacturing difficulty and cost during processing, while shorter ceramic substrates are easier to process, which can reduce manufacturing costs and improve production efficiency.

[0087] (5) A shorter ceramic substrate can reduce the amount of material used, improve material utilization, and further reduce costs.

[0088] It is worth noting that Figure 3 As shown, it is sufficient to ensure that the size of the first ceramic substrate 7 is larger than that of the first antenna 3 to ensure that there is enough space for the first antenna 3 to be placed. Similarly, the second ceramic substrate 8 and the second antenna 4 are also the same.

[0089] Exemplarily, the length of the first shielding cover 5 is 170 mm, and the length of the first ceramic substrate 7 is 110 mm.

[0090] Exemplarily, the length of the second shielding cover 6 is 160 mm, and the length of the first ceramic substrate 7 is 120 mm.

[0091] Such a setting can not only optimize the electromagnetic performance of the antenna, improve the radiation efficiency and directivity of the antenna, but also enhance the mechanical stability and impact resistance of the terminal, while reducing material usage and lowering manufacturing costs.

[0092] In some embodiments, the first antenna 3 and the second antenna 4 are angle-cut circularly polarized antennas, and the angle-cut direction of the first antenna 3 and the angle-cut direction of the second antenna 4 differ by 180 degrees.

[0093] like Figure 2As shown, a cut-angle circularly polarized antenna refers to an antenna in which one or more angles are cut on the metal patch of the antenna to change the radiation pattern of the antenna so that the antenna can radiate and receive circularly polarized waves.

[0094] The cutting angles of the first antenna 3 and the second antenna 4 are symmetrical relative to the center of the mainboard 2. The cutting angle of one antenna is 180 degrees opposite to the cutting angle of the other antenna. This design ensures that no matter which side of the terminal is facing the sky, one antenna's maximum gain radiation direction is always pointed skyward, thus ensuring good communication with the satellite.

[0095] In some embodiments, the outer diameter of the housing 1 is 200 mm, the inner diameter is 170 mm, and the thickness is 30 mm.

[0096] like Figure 3 It can be seen that the lengths of the first shielding cover and the second shielding cover are both less than or equal to the inner diameter of the housing 1 .

[0097] Example 1: When the inner diameter of the housing 1 is 170 mm, the lengths of the first shielding cover and the second shielding cover may be 170 mm.

[0098] Example 2: when the inner diameter of the housing 1 is 170 mm, the lengths of the first shielding cover and the second shielding cover may be 165 mm.

[0099] In some embodiments, the thickness of the first ceramic substrate 7 and the second ceramic substrate 8 may be set to 8 mm.

[0100] In some embodiments, the thickness of the first shielding cover 5 and the second shielding cover 6 can be set to 4 mm.

[0101] The working principle of the above-mentioned airdrop terminal is described in detail below:

[0102] Combine Figure 3 and Figure 6 As shown, the gravity sensor detects the angle between the terminal and the ground plane and transmits the detection signal in real time to the terminal's CPU control unit. The gravity sensor uses the terminal's top surface parallel to the ground as a reference of 0 degrees and the angle between the terminal's top surface and the ground as K0. The CPU control unit controls the switching of the single-pole double-throw switch based on the detection results of the gravity sensor.

[0103] Specifically, an angle redundancy space A is set to prevent frequent switching due to slight vibrations and other reasons. The absolute value of the angle between the upper surface of the terminal and the ground detected by the gravity sensor |K0|. The CPU control unit determines based on the value of |K0| and the preset angle redundancy space A:

[0104] When |K0| increases from less than 90 degrees to 90+A degrees, the CPU control unit controls the single-pole double-throw switch to switch to the second antenna 4 on the lower surface to work;

[0105] When |K0| decreases from greater than 90 degrees to 90-A degrees, the CPU control unit controls the single-pole double-throw switch to switch back to the first antenna 3 on the upper surface to work;

[0106] It is worth noting that to prevent frequent terminal switching, the CPU control unit also sets a time threshold T0. The CPU control unit will trigger the antenna switching action only when the state of |K0| is greater than 90+A degrees or less than 90-A degrees for a period of time exceeding T0.

[0107] This ensures that no matter how the terminal lands, at least one antenna's maximum gain radiation direction is pointed skyward, ensuring good communication with the satellite. In other words, the terminal can automatically switch to the optimal antenna in different landing postures to ensure communication.

[0108] The following describes the process of modeling and simulating the drop-type terminal and its internal antenna solution using 3D electromagnetic simulation software to ensure optimal communication with the satellite in any landing posture.

[0109] Model building process: Use 3D electromagnetic simulation software (such as CST, HFSS, etc.) to build a model of the spray terminal, including the terminal's external structure and internal structure layout;

[0110] Simulation analysis process: Through the simulation software, the performance of the first antenna 3 and the second antenna 4 is simulated and analyzed to obtain the S(1,1) parameters and radiation pattern of the first antenna 3 (such as Figure 7 、 8 As shown), and the S(1,1) parameters and radiation pattern of the second antenna 4) (as shown Figure 9 、 10 shown).

[0111] The S(1, 1) parameter reflects the reflection characteristics of the antenna, and the radiation pattern shows the radiation intensity distribution of the antenna in all directions.

[0112] For the first antenna 3, see Figure 8 The radiation pattern confirms that the maximum gain radiation direction of first antenna 3 points in the positive direction of the Z axis, that is, toward the upper surface of the terminal. When the gravity sensor detects that the upper surface of the terminal is facing the sky, the CPU control unit controls the single-pole double-throw switch to switch to first antenna 3. This ensures that the maximum gain radiation direction of first antenna 3 points toward the sky, achieving optimal communication performance.

[0113] For the second antenna 4, see Figure 10The radiation pattern of antenna 4 confirms that the maximum gain radiation direction of antenna 4 points in the negative direction of the Z axis, that is, toward the bottom surface of the terminal. When the gravity sensor detects that the bottom surface of the terminal is facing the sky, the CPU control unit controls the single-pole double-throw switch to switch to antenna 4. This ensures that the maximum gain radiation direction of antenna 4 points to the sky, achieving optimal communication.

[0114] The embodiment of the present application provides another airdrop terminal, which has the same external structure and substantially the same internal structure as the terminal mentioned above, except that the terminal does not include a gravity detection sensor but a photoelectric tilt detection switch.

[0115] Specifically, an airdrop terminal includes:

[0116] A hollow housing 1 is formed by interlocking two frustum bottom surfaces;

[0117] The mainboard 2 is arranged in the middle of the housing 1;

[0118] The first antenna 3 is provided above the mainboard 2, with its maximum gain radiation direction pointing to the upper surface of the terminal;

[0119] The second antenna 4 is provided below the mainboard 2, with its maximum gain radiation direction pointing toward the lower surface of the terminal;

[0120] A photoelectric tilt detection switch is provided on the main board 2 and is electrically connected to the control end of the single-pole double-throw switch;

[0121] A CPU control unit, which is electrically connected to a radio frequency wireless transceiver and a radio frequency matching circuit in sequence;

[0122] a single-pole double-throw switch, whose input end is electrically connected to the radio frequency matching circuit, and whose output end is electrically connected to the first antenna 3 and the second antenna 4 respectively;

[0123] The photoelectric tilt detection switch detects the angle between the terminal and the ground plane to output a high level or a low level, thereby controlling the single-pole double-throw switch to switch to the first antenna 3 or the second antenna 4 to work.

[0124] In this way, this application adopts a dual-antenna design, combined with a photoelectric tilt detection switch to detect the terminal's posture in real time, and automatically switches to the first antenna or the second antenna pointing to the sky in the direction of maximum gain according to the detection results. Therefore, it can adapt to various unpredictable landing postures and ensure good communication with the satellite in any landing posture, thereby improving the stability and reliability of communication.

[0125] In some embodiments, the photoelectric tilt angle detection switch can be welded on the main board 2 and located in the first shielding cover 5 or the second shielding cover 6.

[0126] The working principle of the above-mentioned air-drop scattering terminal will be described in detail as follows:

[0127] The photoelectric tilt angle detection switch is a sensor capable of sensing the tilt angle of the device. In this scheme, the photoelectric tilt angle detection switch is used to monitor the tilt angle of the terminal relative to the ground.

[0128] In combination with Figure 3 and Figure 11 When the upper surface of the terminal is upward, the photoelectric tilt angle detection switch outputs a high level; when the lower surface of the terminal is upward, the photoelectric tilt angle detection switch outputs a low level. Since the photoelectric tilt angle detection switch is connected to the control end (CTL) of the single-pole double-throw switch, that is, when the photoelectric tilt angle detection switch outputs a high level, the single-pole double-throw switch will select to be connected to the first antenna 3; when the photoelectric tilt angle detection switch outputs a low level, the single-pole double-throw switch will select to be connected to the second antenna 4.

[0129] In this way, in this way, no matter what tilt angle the terminal is in, the antenna with the maximum gain can be automatically selected, and the communication quality between the terminal and the satellite can be improved.

[0130] The words "first", "second", "third" or "module A", "module B", "module C" and the like in the specification and claims are only used to distinguish similar objects, and do not represent a specific order of the objects. It can be understood that the specific order or sequence can be interchanged as allowed, so that the application described herein can be implemented in an order other than that illustrated or described herein.

[0131] The term "comprising" used in the specification and claims should not be interpreted as being limited to the contents listed thereafter; it does not exclude other elements or steps. Therefore, it should be interpreted as specifying the presence of the stated features, integers, steps or components referred to, but does not exclude the presence or addition of one or more other features, integers, steps or components and groups thereof. Therefore, the expression "device comprising device A and B" should not be limited to a device consisting only of components A and B.

[0132] The phrase "one embodiment" or "an embodiment" appearing in the specification means that a particular feature, structure or characteristic described in connection with the embodiment is included in at least one embodiment of the application. Therefore, the phrases "in one embodiment" or "in an embodiment" appearing throughout the specification do not necessarily all refer to the same embodiment, but can refer to the same embodiment. Furthermore, in one or more embodiments, each particular feature, structure or characteristic can be combined in any appropriate manner as would be apparent to one of ordinary skill in the art from this disclosure.

[0133] It is to be understood that the above description is merely a preferred embodiment of the application and the applied technical principles. Those skilled in the art will understand that the application is not limited to the specific embodiments described herein, and that various obvious changes, modifications and substitutions can be made without departing from the scope of the application. Therefore, although the application has been described in detail through the above embodiments, the application is not limited to the above embodiments, and more other equivalent embodiments can be included without departing from the concept of the application, and all belong to the protection scope of the application.

Claims

1. An airdrop terminal, characterized in that: include: A housing (1) having two frustum-shaped bottom surfaces interlocked with each other and having a hollow interior; A main board (2) is arranged in the middle of the housing (1); A first antenna (3) is provided above the mainboard (2), with its maximum gain radiation direction pointing toward the upper surface of the terminal; A second antenna (4) is provided below the mainboard (2), with its maximum gain radiation direction pointing toward the lower surface of the terminal; A gravity detection sensor is provided on the main board (2); A CPU control unit, whose input end is electrically connected to the gravity detection sensor, whose output end is electrically connected to a radio frequency wireless transceiver and a radio frequency matching circuit in sequence, and whose control end is electrically connected to a control end of a single-pole double-throw switch; a single-pole double-throw switch, the input end of which is electrically connected to the radio frequency matching circuit, and the output end of which is electrically connected to the first antenna (3) and the second antenna (4) respectively; The gravity detection sensor detects the angle between the terminal and the ground plane, and controls the single-pole double-throw switch to switch to the first antenna (3) or the second antenna (4) for operation through the CPU control unit.

2. An airdrop terminal, characterized in that: include: A housing (1) having two frustum-shaped bottom surfaces interlocked with each other and having a hollow interior; A main board (2) is arranged in the middle of the housing (1); A first antenna (3) is provided above the mainboard (2), with its maximum gain radiation direction pointing toward the upper surface of the terminal; A second antenna (4) is provided below the mainboard (2), with its maximum gain radiation direction pointing toward the lower surface of the terminal; A photoelectric tilt detection switch is provided on the main board (2); it is electrically connected to the control end of the single-pole double-throw switch; A CPU control unit, which is electrically connected to a radio frequency wireless transceiver and a radio frequency matching circuit in sequence; a single-pole double-throw switch, the input end of which is electrically connected to the radio frequency matching circuit, and the output end of which is electrically connected to the first antenna (3) and the second antenna (4) respectively; The photoelectric tilt detection switch detects the angle between the terminal and the ground plane so as to output a high level or a low level, thereby controlling the single-pole double-throw switch to switch to the first antenna (3) or the second antenna (4) for operation.

3. The terminal according to claim 1 or 2, characterized in that Also includes: A first shielding cover (5) is provided on the upper surface of the mainboard (2) and is used to protect the components of the mainboard (2) and to form a complete reference ground for the first antenna (3) together with the ground layer of the mainboard (2); A second shielding cover (6) is provided on the lower surface of the mainboard (2) and is used to protect the components of the mainboard (2), and together with the ground layer of the mainboard (2) forms a complete reference ground for the second antenna (4). The terminal according to claim 3, wherein: Also includes: a first ceramic substrate (7), disposed on the first shielding cover (5) and used to provide physical support for the first antenna (3); A second ceramic substrate (8) is arranged on the second shielding cover (6) and is used to provide physical support for the second antenna (4). The terminal according to claim 4 , wherein: The first antenna (3) is electroplated on the surface of the first ceramic substrate (7), and the second antenna (4) is electroplated on the surface of the second ceramic substrate (8). The terminal according to claim 5 , wherein: The length of the first ceramic substrate (7) is shorter than the length of the first shielding cover (5); The length of the second ceramic substrate (8) is smaller than the length of the second shielding cover (6).

7. The terminal according to claim 1 or 2, characterized in that: The first antenna (3) and the second antenna (4) are angle-cut circularly polarized antennas, and the angle-cut direction of the first antenna (3) and the angle-cut direction of the second antenna (4) differ by 180 degrees.

8. The terminal according to claim 1 or 2, characterized in that: The outer diameter of the housing (1) is 200 mm, the inner diameter is 170 mm, and the thickness is 30 mm.

9. The terminal according to claim 1 or 2, characterized in that: The terminal is a vertically symmetrical structure centered on the main board (2).

10. The terminal according to claim 3, wherein: The first shielding cover (5) and the second shielding cover (6) are made of stainless steel.

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