Recovery payload measurement system for launch vehicle

Abstract

The application provides a recovery type load measuring system for a carrier rocket, which comprises a collecting unit, a collecting storage unit, a collecting storage unit antenna, a battery, a fiber optic demodulator, a wireless beacon device, a fiber optic strain measuring device, a pressure sensor and an overload sensor; through collecting and storing multiple load parameters in the flight process of the carrier rocket; in the process of returning of a sub-stage, the ground equipment receives short message data sent by the system to obtain the real-time flight position of the sub-stage; after the sub-stage lands, the wireless beacon device is started, the ground equipment identifies the radio signal sent by the wireless beacon device, so that the sub-stage of the rocket is searched and the collecting storage unit installed on the sub-stage is obtained; the data in the collecting storage unit is read and analyzed through the ground test equipment. Therefore, the load bearing condition of the rocket body structure under different attack angles can be directly obtained, and the system has the characteristics of strong independence, high reliability and wide adaptability.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of spacecraft TT&C (Tracking, Telemetry, Command), in particular to a recovery type load measurement system for a launch vehicle. BACKGROUND

[0002] With the vigorous development of aerospace technology, the ability of human beings to enter space and utilize space has been improved year by year. The launch vehicle technology is the mainstream means for human beings to enter space.

[0003] At present, there is no effective means for online measurement of the load bearing condition of the launch vehicle structure during the flight process, so the load design of the launch vehicle still adopts the traditional calculation method. However, the load condition of the launch vehicle directly affects the design of the rocket structure and is directly related to the weight of the rocket structure. Therefore, the load measurement method for the launch vehicle needs to be solved urgently. SUMMARY

[0004] In view of the defects in the prior art, the purpose of the present application is to provide a recovery type load measurement system for a launch vehicle.

[0005] In a first aspect, the present application provides a recovery type load measurement system for a launch vehicle, comprising: a collection unit, a collection storage unit, a collection storage unit antenna, a battery, a fiber optic demodulator, a wireless beacon device, a fiber optic strain measurement device, a pressure sensor, and an overload sensor; wherein:

[0006] The collection unit is arranged in the interstage section of the second stage of the rocket, and is used to collect the pressure, overload, and strain parameters of the rocket;

[0007] The collection storage unit is arranged in the interstage section of the first stage of the rocket, and is used to store the measurement data in the flight test of the rocket;

[0008] The fiber optic demodulator and the fiber optic strain measurement device are arranged in the interstage section of the first stage of the rocket, and are used to measure the strain and load during the flight of the launch vehicle;

[0009] The wireless beacon device is arranged in the interstage section of the first stage of the rocket, and is used to send a radio frequency pulse signal after the first substage of the rocket lands, so that the ground search personnel can search for the first substage of the rocket;

[0010] The pressure sensor is arranged in the fairing ball head, the front and rear cones, and the straight cylinder section, and is used to measure the dynamic pressure during the flight of the launch vehicle;

[0011] The overload sensor is arranged in each cabin section of the rocket, and is used to measure the acceleration response of each cabin section during the flight of the launch vehicle, and to obtain the frequency and mode shape during the flight of the rocket.

[0012] Optionally, the optical fiber demodulator and the optical fiber strain measuring device acquire the load of the interstage section of the substage box through cabin section strain measurement in the rocket flight test.

[0013] Optionally, the application further comprises a Beidou short message system for acquiring the real-time flight position of the substage of the rocket in the return section.

[0014] The Beidou short message system and the wireless beacon device are redundant backups of each other.

[0015] Optionally, the rocket remains in a radio frequency mute state in the active section and does not send electromagnetic radiation signals outward.

[0016] After the first and second stages of the rocket are separated, and when the first and second stages have a sufficient safety distance, the Beidou short message system is started.

[0017] Optionally, the wireless beacon device comprises a beacon device transmitter and a beacon device antenna, and the wireless beacon device is started in a time manner and continuously sends radio signals after the substage of the rocket lands for 30 minutes.

[0018] Optionally, four acquisition and storage unit antennas are arranged in the interstage section of the first stage of the rocket, and the four antennas are arranged at a circumferential interval of 90 degrees.

[0019] Optionally, an independent power distribution mode is adopted, and a battery is separately arranged in the interstage section of the first stage of the rocket.

[0020] Optionally, after the substage of the rocket lands, the measurement data stored in the acquisition and storage unit are read by a ground measurement device to analyze the data in the flight process of the rocket.

[0021] Compared with the prior art, the application has the following beneficial effects:

[0022] The application provides a recovery type load measurement system for a carrier rocket, which is independent of the existing measurement system of the rocket and is used for acquiring and storing multiple load parameters in the flight process of the carrier rocket. BRIEF DESCRIPTION OF DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor based on the provided drawings. Other features, objects and advantages of the present application will become more apparent through reading the following detailed description of the non-limiting embodiments with reference to the following drawings:

[0024] Figure 1 The principle schematic diagram of the recovery type load measuring system for the launch vehicle provided for the embodiments of the present application

[0025] Figure 2 The structural schematic diagram of the recovery type load measuring system for the launch vehicle provided for the embodiments of the present application

[0026] Figure 3 The composition schematic diagram of the wireless beacon device provided for the embodiments of the present application

[0027] Figure 4 The schematic diagram of the installation position of the pressure sensor provided for the embodiments of the present application

[0028] Figure 5 The schematic diagram of the installation position of the overload sensor provided for the embodiments of the present application

[0029] Figure 6 The schematic diagram of the installation position of the optical fiber strain sensor provided for the embodiments of the present application

[0030] In the drawings:

[0031] 1-acquisition unit, 2-acquisition storage unit, 3-acquisition storage unit antenna, 4-battery, 5-optical fiber demodulator, 6-wireless beacon device, 7-optical fiber strain measuring device, 8-pressure sensor, 9-overload sensor DETAILED DESCRIPTION

[0032] The present application will be described in detail below in combination with specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present application. These all belong to the protection scope of the present application.

[0033] It should be noted that when a component is referred to as "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as "connected to" another component, it can be directly connected to or indirectly connected to that other component. Furthermore, a connection can be for both fixing and circuit connection purposes.

[0034] It should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention.

[0035] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of embodiments of the present invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0036] Figure 1 This is a schematic diagram of a recoverable payload measurement system for a launch vehicle provided in an embodiment of this application, as shown below. Figure 1 As shown, the system in this embodiment may include: a data acquisition unit, a data acquisition and storage unit, a data acquisition and storage unit antenna, a battery, a fiber optic demodulator, a wireless beacon device, a fiber optic strain measurement device, a pressure sensor, and an overload sensor. The system is equipped with a single battery for independent power supply. The wireless beacon device consists of a transmitter and an antenna. The pressure sensor is installed on the spherical head, conical section, and straight section of the rocket satellite fairing. The overload sensor and fiber optic strain measurement device are installed on each section of the rocket. The data acquired by the pressure sensor and overload sensor is obtained through the data acquisition unit and transmitted to the data acquisition and storage unit for storage. During rocket flight, strain data is acquired using the fiber optic strain measurement device, processed by the fiber optic demodulator, and then transmitted to the data acquisition and storage unit for storage. To obtain the position information of the first stage of the rocket, the system is equipped with BeiDou short message service and transmits the real-time position information of the rocket through the data acquisition and storage unit antenna. After the first stage of the rocket lands, the wireless beacon device is activated, and ground search personnel use dedicated ground equipment to locate the position of the data acquisition and storage unit based on the monitored pulse signals and their strength.

[0037] Figure 2A structure diagram of a load measuring system for a launch vehicle is provided in the embodiments of the present application, as shown in Figure 2 The system can include a collecting unit 1, a collecting storage unit 2, a collecting storage unit antenna 3, a battery 4, a fiber demodulator 5, a wireless beacon device 6, a fiber strain measuring device 7, a pressure sensor 8, and an overload sensor 9. The pressure sensor 8 is installed on the ball head, the cone section, and the straight cylinder section of the fairing of the rocket satellite. The overload sensor 9 is installed on the fairing of the rocket satellite, the interface between the satellite and the rocket, the inter-box section of the first stage, the inter-box section of the second stage, the inter-stage section between the first and second stages, and the tail section of the first stage. The fiber strain measuring device 7 is installed on the inter-box section of the first stage. The dynamic pressure and the dynamic response during the flight of the rocket are collected by the pressure sensor 8 and the overload sensor 9, the data is collected by the collecting unit 1, and the data is transmitted to the collecting storage unit 2. The strain of the inter-box section of the first stage is measured by the fiber strain measuring device 7, and the data is directly transmitted to the collecting storage unit 2.

[0038] For example, after the separation of the first and second stages of the rocket, the Beidou short message function of the system is started, and the implementation position information of the rocket is transmitted downward through the collecting storage unit antenna. After the first sub-stage lands, the wireless beacon device is started in a time manner, and the ground search personnel searches for the first sub-stage according to the special ground equipment. After the ground personnel obtain the collecting storage unit installed on the first sub-stage, the flight data in the collecting storage unit is read and analyzed by using the ground test equipment.

[0039] For example, in the above load measuring system, four collecting storage unit antennas are arranged on the inter-box section of the first stage of the rocket, and the four antennas are arranged at a circumferential interval of 90° to improve the wireless signal transmission capability during the irregular motion of the rocket in the return section.

[0040] For example, in the above load measuring system, self-distribution is adopted, and a battery is separately arranged on the inter-box section of the first stage of the rocket, and the power supply of the rocket is not required.

[0041] For example, during the specific measurement, the above measuring system keeps the radio frequency in a mute state in the main active section of the rocket, does not send electromagnetic radiation signals outward, and has no influence on the electromagnetic compatibility of the main task of the rocket. After the separation of the first and second stages of the rocket, the Beidou short message function of the system is started after a sufficient safety distance is left between the first and second stages.

[0042] Figure 3 A composition diagram of a wireless beacon device is provided in the embodiments of the present application, as shown in Figure 3 The wireless beacon device includes a beacon device transmitter and a beacon device antenna, the Beidou short message system is used to obtain the real-time flight position of the first sub-stage of the rocket in the return section, and the wireless beacon device is used to obtain the landing position of the first sub-stage. The Beidou short message system and the wireless beacon device are mutually redundant backups, and the searching capability of the first sub-stage of the rocket is improved.

[0043] For example, the wireless beacon device can be activated periodically 30 minutes after the first stage of the rocket lands, continuously transmitting radio signals so that ground search personnel can use specialized ground equipment to locate the first stage of the rocket.

[0044] The recoverable payload measurement system for launch vehicles in this embodiment can operate independently of the existing rocket measurement system. It collects and stores multiple payload parameters during the launch vehicle's flight. During the first-stage reentry, ground equipment receives short message data from this system to obtain the real-time flight position of the first stage. After the first stage lands, the wireless beacon device activates. Ground equipment identifies the radio signals emitted by the beacon device to locate the first stage and access the data acquisition and storage unit installed on it. Researchers use ground testing equipment to read and analyze the data within the acquisition and storage unit. This system features independence, high reliability, and wide applicability.

[0045] Figure 4 This is a schematic diagram of the pressure sensor installation location provided in an embodiment of this application, as shown below. Figure 4 As shown, pressure sensors are installed on the spherical head, front cone, and straight section of the satellite fairing; by using pressure sensors installed on the rocket, the dynamic pressure during the launch vehicle's flight is measured, and the flight angle of attack during the rocket flight test is obtained.

[0046] Figure 5 This is a schematic diagram of the installation position of the overload sensor provided in an embodiment of this application, as shown below. Figure 5 As shown, overload sensors installed on the rocket are used to obtain the frequencies and mode shapes during rocket flight tests. Specifically, overload sensors are installed in each section of the rocket to measure the acceleration response of each section during the launch vehicle's flight, thereby obtaining the frequencies and mode shapes during rocket flight.

[0047] Figure 6 This is a schematic diagram of the installation position of the fiber optic strain sensor provided in the embodiments of this application, as shown below. Figure 6 As shown, an optical fiber strain measurement device and an optical fiber demodulator are installed in the first-stage inter-box section of the rocket to measure the strain of the first-stage inter-box section during the flight of the launch vehicle, thereby obtaining the load of the first-stage inter-box section during the flight of the rocket.

[0048] This embodiment can directly obtain the load-bearing conditions of the rocket body structure at different angles of attack by measuring the aerodynamic forces, dynamic response, and strain of the sections during rocket flight, and by using the rocket load calculation model, which can be used for launch vehicle load condition margin analysis.

[0049] The above is the core idea of the present application. In order to make the above-mentioned purpose, features and advantages of the present application more obvious and easy to understand, the technical solutions in the embodiments of the present application will be described clearly and completely below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0050] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts between the various embodiments can be referred to each other. The above description of the disclosed embodiments enables those skilled in the art to implement or use the present application. Various modifications to the embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

[0051] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various modifications or changes within the scope of the claims, which does not affect the essential content of the present application.

Claims

1. A recoverable payload measurement system for launch vehicles, characterized in that, include: Acquisition unit, acquisition and storage unit, acquisition and storage unit antenna, battery, fiber optic demodulator, wireless beacon device, fiber optic strain measurement device, pressure sensor, overload sensor, BeiDou short message system; among which: The acquisition unit is located in the second stage compartment of the rocket and is used to collect rocket pressure, overload, and strain parameters. By measuring the aerodynamic force, dynamic response and compartment strain during rocket flight, and using the rocket load calculation model, the load-bearing conditions of the rocket body structure under different angles of attack are directly obtained. The load-bearing conditions under different angles of attack are used to perform load condition margin analysis of the launch vehicle. The data acquisition and storage unit is located in the first-stage compartment of the rocket and is used to store measurement data during rocket flight tests. After the first stage of the rocket lands, the measurement data stored in the data acquisition and storage unit is read by ground measurement equipment to analyze the data during the rocket flight. The fiber optic demodulator and the fiber optic strain measurement device are installed in the first stage compartment of the rocket and are used to measure the strain and load during the flight of the launch vehicle. The wireless beacon device is installed in the first stage compartment of the rocket and is used to send radio frequency pulse signals after the first stage of the rocket lands, so that ground search personnel can locate the first stage of the rocket. The pressure sensors are installed at the fairing ball head, front and rear cones, and straight cylindrical section, and are used to measure the dynamic pressure during the flight of the launch vehicle; The overload sensors are installed in each section of the rocket to measure the acceleration response of each section during the flight of the launch vehicle, and to obtain the frequency and mode shape of the rocket during flight. The BeiDou short message system is used to obtain the real-time flight position of the first stage of a rocket's return phase. The landing location of the first stage of the rocket is obtained through the wireless beacon device, wherein the Beidou short message system and the wireless beacon device are redundant backups of each other.

2. The recoverable payload measurement system for a launch vehicle according to claim 1, characterized in that, The fiber optic demodulator and the fiber optic strain measurement device obtain the load of the first-stage inter-box section during rocket flight testing by measuring the strain of the compartment.

3. The recoverable payload measurement system for a launch vehicle according to claim 1, characterized in that, Maintain radio frequency silence during the rocket's active phase and do not transmit electromagnetic radiation signals. After the first and second stages of the rocket separate, and after there is a sufficient safe distance between the first and second stages, the BeiDou short message system is activated.

4. The recoverable payload measurement system for a launch vehicle according to claim 1, characterized in that, The wireless beacon device includes a beacon transmitter and a beacon antenna. The wireless beacon device is activated periodically and continuously transmits radio signals 30 minutes after the first stage of the rocket lands.

5. The recoverable payload measurement system for a launch vehicle according to any one of claims 1-4, characterized in that, Four data acquisition and storage unit antennas are installed in the first stage compartment of the rocket, and the four antennas are arranged at 90° intervals around the perimeter.

6. The recoverable payload measurement system for a launch vehicle according to any one of claims 1-4, characterized in that, It adopts an independent power distribution method, with batteries separately configured in the first-stage compartment of the rocket.

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