CN116026194A

CN116026194A - Missile GPS signal state simulation device

Info

Publication number: CN116026194A
Application number: CN202310003837.0A
Authority: CN
Inventors: 易祺兵; 陈功
Original assignee: Chongqing Aerospace Launch Vehicle Electronic Technology Co ltd
Current assignee: Chongqing Aerospace Launch Vehicle Electronic Technology Co ltd
Priority date: 2023-01-03
Filing date: 2023-01-03
Publication date: 2023-04-28

Abstract

The invention belongs to the technical field of missile simulation. The missile GPS signal state simulation device comprises a GPS roller assembly, a roller supporting seat, a power system and four diversity devices; the GPS roller assembly comprises a roller, a missile-borne GPS and a roller spindle; the roller is fixedly arranged on the roller main shaft, and the missile-borne GPS is fixedly arranged on the roller; the roller main shaft is rotationally arranged on the roller supporting seat; one end of the main shaft of the roller is provided with an electric slip ring, the other end of the main shaft of the roller is connected with the power system, and the missile-borne GPS is connected with four diversity equipment through the electric slip ring; the drum simulates the rotation state of the missile under the driving of the power system, and the missile-borne GPS signal is transmitted to the four-diversity equipment through the electric slip ring. According to the invention, the autorotation state of the missile flight process is simulated on the ground, the missile-borne GPS is installed on the roller, GPS signals are transmitted to the four-diversity equipment through the electric slip ring, and the feasibility of GPS analysis hardware and analysis algorithm of the four-diversity equipment is verified according to the received GPS signals.

Description

Missile GPS signal state simulation device

Technical Field

The invention belongs to the technical field of missile simulation, and relates to a missile GPS signal state simulation device.

Background

In the missile flight process, positioning is carried out by means of a missile-borne GPS, as shown in figure 1, the position of the missile body 1, in which the GPS antenna 2 is embedded, is a cylindrical surface, and the GPS antennas 2 are uniformly arranged on the same circular cross section surface. There are 3 arrangements of its GPS: an adjacent 180 DEG arrangement, namely 2 GPS antennae are symmetrically arranged; the adjacent 120-degree GPS antennas are symmetrically arranged, namely 3 GPS antennas are arranged in total; the adjacent 90 deg. arrangement, i.e. the total of 4 GPS antennas are symmetrically arranged. When flying, the missile can autorotate, so that the GPS antenna of the missile rotates along with the missile. The missile is influenced by the working state and the external environment, the rotation speed of the missile is between 10 and 100r/min, and the rotation state can be uniform circular motion or variable circular motion.

The four-diversity equipment is key equipment for positioning analysis and gain of a missile-borne GPS, the feasibility and the reliability of the four-diversity equipment are directly related to success and failure of missile launching, however, because of the particularity of a missile, the verification of the four-diversity equipment cannot be directly verified through a live missile and can only be verified through a ground simulation system, so that a device capable of simulating GPS signal state simulation when the missile flies is needed.

Disclosure of Invention

Therefore, the invention aims to realize ground simulation of missile GPS signals, meets the requirement of verification of four diversity equipment, and provides a missile GPS signal state simulation device.

In order to achieve the above purpose, the present invention provides the following technical solutions:

a missile GPS signal state simulation device comprises a GPS roller assembly, a roller supporting seat, a power system and four diversity devices; the GPS roller assembly comprises a roller, a missile-borne GPS and a roller spindle; the roller is fixedly arranged on the roller main shaft, and the missile-borne GPS is fixedly arranged on the roller; the roller main shaft is rotationally arranged on the roller supporting seat; one end of the main shaft of the roller is provided with an electric slip ring, the other end of the main shaft of the roller is connected with the power system, and the missile-borne GPS is connected with four diversity equipment through the electric slip ring; the drum simulates the rotation state of the missile under the driving of the power system, and the missile-borne GPS signal is transmitted to the four-diversity equipment through the electric slip ring.

Further, the number of the missile-borne GPS is multiple, and the missile-borne GPS is circumferentially and uniformly distributed on the roller.

Further, the power system comprises a large belt wheel, a manual idle wheel, an electric idle wheel, a hand-operated wheel and a motor; the large belt wheel is sleeved on the roller main shaft, and the manual idler wheel and the electric idler wheel are both rotatably arranged on the roller supporting seat;

the large belt wheel is respectively in transmission connection with the manual idler wheel and the electric idler wheel through a belt, the manual idler wheel is in transmission connection with the hand-operated wheel, the electric idler wheel is in transmission connection with a motor, and the motor or the manual shaking hand-operated wheel drives the roller to rotate.

Further, the motor is connected with a variable frequency speed regulator for controlling the operation of the motor.

Further, the number of the missile-borne GPS is 6, and the missile-borne GPS is embedded on the outer wall of the roller.

Further, a cable groove is formed in the main shaft of the roller, and the connection cable of the missile-borne GPS is arranged in the cable groove and connected with the electric slip ring.

The invention has the beneficial effects that:

1. the missile GPS signal state simulation device realizes the simulation of the autorotation state of the missile in the flying process of the ground, a missile-borne GPS is installed on the roller, GPS signals are transmitted to the four diversity equipment through the electric slip ring, and the feasibility of the GPS analysis hardware and the analysis algorithm of the four diversity equipment is verified according to the received GPS signals.

2. The missile GPS signal state simulation device controls the running state of the motor by adopting the variable frequency speed regulator, further controls the rotation of the roller, can change the speed at a constant speed, can rotate forward or reverse, can simulate different rotation speeds in the missile flight process, can also assign a static state, and performs feasibility verification of four diversity equipment. The power system adopts two driving modes of electric and manual operation, and the driving belt is not required to be removed or replaced after a certain control mode is specified, so that the operation is simple and easy to learn and use.

Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention. The objects and other advantages of the invention may be realized and obtained by means of the instrumentalities and combinations particularly pointed out in the specification.

Drawings

For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in the following preferred detail with reference to the accompanying drawings, in which:

FIG. 1 is a schematic diagram of a GPS antenna on a missile;

FIG. 2 is a schematic diagram of a missile GPS signal state simulation device in the invention;

FIG. 3 is a side view of FIG. 2;

FIG. 4 is a schematic view of a GPS roller assembly according to the present invention;

FIGS. 5 and 6 are schematic diagrams of power systems;

fig. 7 is a schematic view of an electrical slip ring installation.

Reference numerals: 1-missile body; a 2-GPS antenna; 3-GPS roller assembly; 4-a roller support base; 5-a power system; 6-an electrical slip ring; 31-a roller; 32-missile-borne GPS; 33-a drum spindle; 51-a large belt wheel; 52-a manual idler; 53-a hand wheel; 54-an electric idler; 55-motor; 56-a variable frequency speed regulator; 61-an electrical slip ring stator; 62-electrical slip ring rotor.

Detailed Description

Other advantages and effects of the present invention will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present invention with reference to specific examples. The invention may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present invention. It should be noted that the illustrations provided in the following embodiments merely illustrate the basic idea of the present invention by way of illustration, and the following embodiments and features in the embodiments may be combined with each other without conflict.

Wherein the drawings are for illustrative purposes only and are shown in schematic, non-physical, and not intended to limit the invention; for the purpose of better illustrating embodiments of the invention, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the size of the actual product; it will be appreciated by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted.

The same or similar reference numbers in the drawings of embodiments of the invention correspond to the same or similar components; in the description of the present invention, it should be understood that, if there are terms such as "upper", "lower", "left", "right", "front", "rear", etc., that indicate an azimuth or a positional relationship based on the azimuth or the positional relationship shown in the drawings, it is only for convenience of describing the present invention and simplifying the description, but not for indicating or suggesting that the referred device or element must have a specific azimuth, be constructed and operated in a specific azimuth, so that the terms describing the positional relationship in the drawings are merely for exemplary illustration and should not be construed as limiting the present invention, and that the specific meaning of the above terms may be understood by those of ordinary skill in the art according to the specific circumstances.

Referring to fig. 2 to 7, a missile GPS signal state simulation device includes a GPS drum assembly 3, a drum support 4, a power system 5, and a four-diversity device; the GPS roller assembly 3 comprises a roller 31, a missile-borne GPS32 and a roller main shaft 33; the roller 31 is fixedly arranged on a roller main shaft 33 through a flange, and the missile-borne GPS32 is fixedly arranged on the roller 31; the roller main shaft 33 is rotatably installed on the roller support seat 4; one end of the roller main shaft 33 is provided with an electric slip ring 6, the other end is connected with the power system 5, and the missile-borne GPS32 is connected with four diversity equipment through the electric slip ring 6; the drum 31 simulates the missile rotation state under the drive of the power system 5, and the missile-borne GPS32 signal is transmitted to the four-diversity equipment through the electric slip ring 6.

Wherein, the number of the missile-borne GPS32 is 6, and the missile-borne GPS is uniformly distributed and embedded on the outer wall of the roller 31 in a circumference manner; and the feasibility of the four-diversity equipment is verified by selecting different combinations of missile-borne GPS arrangement modes.

In this embodiment, the power system 5 includes a large belt wheel 51, a manual idle wheel 52, an electric idle wheel 54, a hand-operated wheel, and a motor 55; the large belt wheel 51 is sleeved on the roller main shaft 33, and the manual idler wheel 52 and the electric idler wheel 54 are both rotatably arranged on the roller support seat 4; the large belt wheel 51 is respectively connected with a manual idler wheel 52 and an electric idler wheel 54 in a transmission way through a belt, the manual idler wheel 52 is connected with the manual idler wheel in a transmission way, the electric idler wheel 54 is connected with a motor 55 in a transmission way, and the manual idler wheel is driven by the motor 55 or the manual shaking hand wheel to rotate. Wherein, the motor 55 is connected with a variable frequency speed regulator 56 for controlling the operation of the motor 55. The manual mode control of the rotation of the drum 31 is achieved by manually driving the handwheel 53; the rotation of the motor-driven mode control drum 31 is achieved by the driving of the motor 55.

The electric slip ring rotor 62 is fixedly connected with the roller main shaft 33, a cable groove is formed in the roller main shaft 33, and a connecting cable of the missile-borne GPS32 is installed in the cable groove and connected with the electric slip ring rotor 62; the electrical slip ring stator 61 is connected to the four diversity apparatus by a cable to transmit the missile-borne GPS32 signal to the four diversity apparatus.

Finally, it is noted that the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications and equivalents may be made thereto without departing from the spirit and scope of the present invention, which is intended to be covered by the claims of the present invention.

Claims

1. A missile GPS signal state simulation device is characterized in that: the device comprises a GPS roller assembly, a roller supporting seat, a power system and four diversity equipment; the GPS roller assembly comprises a roller, a missile-borne GPS and a roller spindle; the roller is fixedly arranged on the roller main shaft, and the missile-borne GPS is fixedly arranged on the roller; the roller main shaft is rotationally arranged on the roller supporting seat; one end of the main shaft of the roller is provided with an electric slip ring, the other end of the main shaft of the roller is connected with the power system, and the missile-borne GPS is connected with four diversity equipment through the electric slip ring; the drum simulates the rotation state of the missile under the driving of the power system, and the missile-borne GPS signal is transmitted to the four-diversity equipment through the electric slip ring.

2. The missile GPS signal state simulation device according to claim 1, wherein: the missile-borne GPS is multiple and uniformly distributed on the roller in a circumference manner.

3. The missile GPS signal state simulation device according to claim 1, wherein: the power system comprises a large belt wheel, a manual idler wheel, an electric idler wheel, a hand-operated wheel and a motor; the large belt wheel is sleeved on the roller main shaft, and the manual idler wheel and the electric idler wheel are both rotatably arranged on the roller supporting seat;

4. A missile GPS signal condition simulation device according to claim 3, wherein: the motor is connected with a variable frequency speed regulator for controlling the operation of the motor.

5. The missile GPS signal state simulation device according to claim 2, wherein: and 6 missile-borne GPS are embedded on the outer wall of the roller.

6. The missile GPS signal state simulation device according to claim 1, wherein: the drum spindle is provided with a cable groove, and the connection cable of the missile-borne GPS is arranged in the cable groove and connected with the electric slip ring.