A universal hypersonic flight test system

Abstract

The application relates to a universal hypersonic flight test system, which comprises a payload system, a ground system and a test carrier platform, and comprises a ground comprehensive control machine, a launching vehicle, a measurement and launch control vehicle, a telemetry vehicle and an external measurement vehicle; the ground comprehensive control machine is a central node of the whole test system and is used for task planning, parameter instruction issuing and data recovery analysis; a measurement and launch control front end and a carrier are arranged on the launching vehicle; the measurement and launch control front end is used for executing instruction signals transmitted by the measurement and launch control vehicle; the carrier comprises a carrying platform and a test load; the test load is installed in a fairing of the test platform; and the test platform provides a flight environment, power supply and communication conditions for the test load. The system provided by the application is designed to be universal and automatic, the system is high in working efficiency, and various types of hypersonic flight tests can be conveniently carried out.

Description

Technical Field

[0001] This invention relates to a universal hypersonic flight test system, belonging to the field of aerospace launch technology. Background Technology

[0002] Hypersonic vehicles refer to all types of aircraft capable of sustained flight at speeds of at least Mach 5 in near-space. These vehicles, with their high maneuverability, rapid reaction speed, long range, and excellent penetration capabilities, possess significant advantages in enriching combat styles, enhancing combat deterrence, driving technological development, and shortening transportation time. They have become a key development area and a competitive focus in the domestic and international aerospace fields.

[0003] A hypersonic vehicle flight test system typically includes a payload, a launch platform, launch and control equipment, and ground telemetry / external measurement equipment. The payload is the core of the flight test system and is generally a glide vehicle, cruise vehicle, or scientific experimental equipment used to complete demonstration flights or collect scientific data. The launch platform provides the initial operating environment for the payload. After reaching the payload's operating environment, the payload separates from the launch vehicle, and the payload completes subsequent flight missions. The remaining equipment provides support and assistance to the flight test system.

[0004] Currently, the main flight test platforms available for hypersonic research include launch vehicle platforms, air-launched rocket platforms, and ground-launched rocket platforms. Launch vehicles offer strong carrying capacity, but limited opportunities for carrying them and high costs significantly restrict the frequency and accessibility of flight tests. Air launch offers better mission adaptability, and the launch vehicle platform can provide a favorable initial flight environment, but it requires a powerful aircraft platform for support, resulting in high testing costs and the need for multi-departmental cooperation. Ground-launched small rocket platforms are characterized by self-launch and fewer support conditions, but suffer from poor payload adaptability. Furthermore, hypersonic vehicles operate in complex environments with intricate dynamic coupling mechanisms and characteristics, and different test payloads exhibit different mission profiles. Ground-based test launch platforms struggle to meet diverse launch requirements, often necessitating redesign of the launch system to adapt to varied payload flight conditions. This leads to long development cycles, high development costs, and inconvenience for users. Summary of the Invention

[0005] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a universal hypersonic flight test system. It adopts a modular and universal design, is compatible with the diverse mechanical, electrical and separation requirements of test payloads, and uses optimization algorithms to automatically plan the counterweight and launch parameters of the launch platform. This achieves the universality of the hypersonic flight platform, meets the mission requirements of test payloads under various working conditions, and avoids the waste of human and material resources caused by the repeated development of test platforms due to the diversity of test payload requirements.

[0006] The solution of the present invention is:

[0007] A general-purpose hypersonic flight test system includes a payload system, a ground system, and a test launch platform.

[0008] The ground system is used for flight test support, providing test environment simulation, flight program injection, system transfer, parameter setting, launch platform erection, launch control, and data retrieval for the launch platform. It includes the ground control unit, launch vehicle, telemetry and control vehicle, telemetry vehicle, and external measurement vehicle.

[0009] The ground control unit is the central node of the entire test system, used for mission planning, parameter command issuance, and data collection and analysis.

[0010] The launch vehicle is equipped with a telemetry, launch and control front-end and a carrier. The telemetry, launch and control front-end is used to execute the command signals transmitted from the telemetry, launch and control vehicle. The carrier includes a carrier platform and a test payload. The test payload is installed in the fairing of the test platform. The test platform provides the test payload with the flight environment, power supply and communication conditions.

[0011] Telemetry vehicles and external measurement vehicles are used to receive telemetry data before and during flight;

[0012] The testing system includes mission planning and flight testing;

[0013] During mission planning, the mission planning unit built into the integrated control computer is used to automatically plan the mission. The mission planning unit has built-in aerodynamic parameters, mass parameters, load parameters, dynamic performance parameters and control program parameters of the launch vehicle. The genetic optimization algorithm is used to optimize the design of the counterweight mass parameters, launch parameters and timing parameters. The flight performance under standard and extreme pull conditions is used as the index constraint to generate the optimal flight trajectory that meets the working conditions of the test load.

[0014] After completing flight performance calculations on the ground control aircraft, the structural strength of the launch vehicle is verified, the flight test mission planning is completed, and decisions are made regarding the flight test.

[0015] After confirming the execution of the flight mission, a counterweight is installed on the test launch platform, and the parameters output by the mission planning unit are sent to the launch vehicle and the telemetry and control vehicle, while the standard flight trajectory is sent to the telemetry vehicle and the external measurement vehicle.

[0016] After completing the flight test preparations, the launch vehicle, telemetry vehicle, and launch control vehicle traveled in formation to the launch site. After the launch vehicle was positioned according to the predetermined launch azimuth angle, the launch vehicle was erected to the designated launch angle. After entering the launch process, the launch vehicle was tested and launched, and the ignition and takeoff command was issued at the predetermined time. The launch vehicle was driven off the orbit by the rocket engine and flew according to the predetermined sequence. After meeting the payload working conditions, the test payload was separated and autonomously flown.

[0017] After entering the launch process, the telemetry vehicle and the external measurement vehicle track the launch vehicle and test payload according to the predetermined trajectory, and receive and store telemetry data;

[0018] After the flight test is completed, the test mission is automatically analyzed by collecting telemetry data and launch control data to generate a mission report for user decision-making.

[0019] Furthermore, the payload system is the core of the flight test system, specifically for hypersonic test vehicles.

[0020] Furthermore, the test launch platform provides the initial working environment for the payload. After reaching the payload's working environment, the payload separates from the launch vehicle, and the payload completes its subsequent flight mission.

[0021] Furthermore, the launch platform includes a steering system and a telemetry system. The steering system is used for attitude control of the launch platform, and the telemetry system is used for acquiring test data and monitoring its status.

[0022] Furthermore, the ground control unit is used to combine the test mission instructions issued by the user with the capabilities of the launch platform to perform mission evaluation, performance prediction, parameter design and configuration, receive telemetry signals, test data, and issue control instructions.

[0023] Furthermore, the user transmits the flight conditions, mass characteristics, and power supply requirements of the test payload to the ground control unit, which then automatically performs mission planning and performance simulation analysis based on the capabilities and characteristics of the launch platform.

[0024] Furthermore, a counterweight position is reserved in the counterweight compartment of the launch platform to cope with the release mission under different flight altitudes, speeds and attitudes. During mission planning, the flight conditions, mass characteristics and performance parameters of the test payload and the launch platform are used as inputs, and the counterweight mass and installation position on the launch platform are used as output parameters. Optimization algorithms such as genetic algorithms are used to automatically optimize the design to ensure that the counterweight mass is minimized and the control system rudder usage is minimized while meeting the payload release conditions and flight load.

[0025] Furthermore, after the ground control unit completes the mission evaluation, it will provide feedback on the installation location, weight, and parameter results of the counterweight, and generate a report on the mission evaluation results, including flight performance simulation and power analysis, for user decision-making.

[0026] Furthermore, if the flight mission is deemed feasible after evaluation, the corresponding counterweights will be installed in the counterweight compartment, the payload will be placed inside the fairing, and the parameters will be loaded into the integrated control system of the launch platform via the ground integrated control unit to complete the mission planning.

[0027] Furthermore, after the ground support system transports the launch vehicle to the launch site, the launch vehicle is erected in position according to the firing direction and launch angle specified in the parameters, and awaits the launch command; the telemetry and control vehicle is placed outside the safety zone to the side of the launch vehicle, and is used to conduct system testing and launch control of the launch vehicle; the telemetry vehicle is placed outside the safety zone of the launch site, arranged to the side along the firing direction, and is used to receive telemetry information of the launch vehicle and payload issued by the launch vehicle on the ground and during the takeoff phase; the external telemetry vehicle is placed between the launch point and the landing point, outside the airway safety zone, and is used to receive telemetry information of the launch vehicle and payload in the phase after takeoff.

[0028] The advantages of this invention compared to the prior art are:

[0029] (1) This invention designs a flight test system suitable for diverse hypersonic flight tests. The system consists of a general-purpose test platform and a ground vehicle-mounted support system, forming a unified and organically combined whole. Each system is centered on the ground integrated control unit, which automatically performs task planning using the built-in task planning unit of the integrated control unit, generating test task parameters such as counterweight mass, counterweight position, and timing, and can distribute the task parameters to other systems within the system. After the test is completed, each system transmits the test results to the integrated control unit for task analysis, with a high degree of automation.

[0030] (2) The present invention has a reserved counterweight compartment on the carrier platform, and counterweight blocks are installed in the counterweight compartment. The counterweight blocks can be freely combined and installed and fixed at any position along the axial direction of the compartment section to meet the diverse separation conditions of the test load and the requirements of the carrier platform control system.

[0031] (3) The integrated control unit of the present invention has a built-in task planning unit that can design the optimal flight trajectory that meets the load constraints and terminal condition constraints during flight based on the task parameters using a genetic optimization algorithm, and transmit the relevant parameters to the launch vehicle, the launch and control vehicle and the telemetry vehicle through optical fiber, thereby reducing the degree of personnel involvement, freeing personnel from complex task analysis and reducing the probability of errors in data transmission. Attached Figure Description

[0032] Figure 1 A flowchart of the flight test system workflow;

[0033] Figure 2 It is a segmented fairing;

[0034] Figure 3 This is a structural diagram of the counterweight compartment;

[0035] Figure 4 This is a flight test profile of a hypersonic vehicle.

[0036] Figure 5 For the relationship and data exchange of hypersonic vehicle flight test systems. Detailed Implementation

[0037] The present invention will be further described below with reference to the embodiments.

[0038] like Figure 1-5 As shown, a general-purpose hypersonic flight test system includes a payload system, a ground system, and a test launch platform.

[0039] The ground system is used for flight test support, providing test environment simulation, flight program injection, system transfer, parameter setting, launch platform erection, launch control, and data retrieval for the launch platform. It includes the ground control unit, launch vehicle, telemetry and control vehicle, telemetry vehicle, and external measurement vehicle.

[0040] The ground control unit is the central node of the entire test system, used for mission planning, parameter command issuance, and data collection and analysis.

[0041] The launch vehicle is equipped with a telemetry, launch and control front-end and a carrier. The telemetry, launch and control front-end is used to execute the command signals transmitted from the telemetry, launch and control vehicle. The carrier includes a carrier platform and a test payload. The test payload is installed in the fairing of the test platform. The test platform provides the test payload with the flight environment, power supply and communication conditions.

[0042] Telemetry vehicles and external measurement vehicles are used to receive telemetry data before and during flight;

[0043] The testing system includes mission planning and flight testing;

[0044] During mission planning, the mission planning unit built into the integrated control computer is used to automatically plan the mission. The mission planning unit has built-in aerodynamic parameters, mass parameters, load parameters, dynamic performance parameters and control program parameters of the launch vehicle. The genetic optimization algorithm is used to optimize the design of the counterweight mass parameters, launch parameters and timing parameters. The flight performance under standard and extreme pull conditions is used as the index constraint to generate the optimal flight trajectory that meets the working conditions of the test load.

[0045] After completing flight performance calculations on the ground control aircraft, the structural strength of the launch vehicle is verified, the flight test mission planning is completed, and decisions are made regarding the flight test.

[0046] After confirming the execution of the flight mission, a counterweight is installed on the test launch platform, and the parameters output by the mission planning unit are sent to the launch vehicle and the telemetry and control vehicle, while the standard flight trajectory is sent to the telemetry vehicle and the external measurement vehicle.

[0047] After completing the flight test preparations, the launch vehicle, telemetry vehicle, and launch control vehicle traveled in formation to the launch site. After the launch vehicle was positioned according to the predetermined launch azimuth angle, the launch vehicle was erected to the designated launch angle. After entering the launch process, the launch vehicle was tested and launched, and the ignition and takeoff command was issued at the predetermined time. The launch vehicle was driven off the orbit by the rocket engine and flew according to the predetermined sequence. After meeting the payload working conditions, the test payload was separated and autonomously flown.

[0048] After entering the launch process, the telemetry vehicle and the external measurement vehicle track the launch vehicle and test payload according to the predetermined trajectory, and receive and store telemetry data;

[0049] After the flight test is completed, the test mission is automatically analyzed by collecting telemetry data and launch control data to generate a mission report for user decision-making.

[0050] The payload system is the core of the flight test system, specifically for hypersonic test vehicles.

[0051] The test launch platform provides the initial working environment for the payload. After the payload reaches the working environment, the payload separates from the launch vehicle and completes the subsequent flight mission.

[0052] The launch platform includes a steering system and a telemetry system. The steering system is used for attitude control of the launch platform, and the telemetry system is used for acquiring test data and monitoring its status.

[0053] The ground control unit is used to combine the test mission instructions issued by the user with the capabilities of the carrier platform to perform mission evaluation, performance prediction, parameter design and configuration, receive telemetry signals, test data and issue control instructions.

[0054] Users transmit flight conditions, mass characteristics, and power supply requirements of the test payload to the ground control unit, which then automatically performs mission planning and performance simulation analysis based on the capabilities of the launch platform.

[0055] A counterweight position is reserved in the counterweight compartment of the launch platform to cope with the release mission of the payload under different flight altitude, flight speed and attitude conditions. During mission planning, the flight conditions, mass characteristics and performance parameters of the test payload and the launch platform are used as inputs, and the counterweight mass and installation position on the launch platform are used as output parameters. The optimization design is automatically performed using optimization algorithms such as genetic algorithms to ensure that the counterweight mass is minimized and the control system rudder usage is minimized while meeting the payload release conditions and flight load conditions.

[0056] After the ground control unit completes the mission evaluation, it will provide feedback on the installation location, weight, and parameter results of the counterweight, and generate a report on the mission evaluation, including flight performance simulation and power analysis, for user decision-making.

[0057] If the flight mission is deemed feasible after evaluation, the corresponding counterweights will be installed in the counterweight compartment, the payload will be placed in the fairing, and the parameters will be loaded into the integrated control system of the launch platform via the ground integrated control unit to complete the mission planning.

[0058] After the ground support system transports the launch vehicle to the launch site, the launch vehicle is erected in position according to the firing direction and launch angle specified in the parameters and awaits the launch command. The telemetry and control vehicle is placed outside the safety zone to the side of the launch vehicle and is used to conduct system testing and launch control of the launch vehicle. The telemetry vehicle is placed outside the safety zone of the launch site and arranged to the side along the firing direction. It is used to receive telemetry information of the launch vehicle and payload issued by the launch vehicle on the ground and during the takeoff phase. The external telemetry vehicle is placed between the launch point and the landing point, outside the airway safety zone, and is used to receive telemetry information of the launch vehicle and payload in the phase after takeoff.

[0059] Specific experimental methods include:

[0060] Step 1: Based on the flight state requirements of the test load, with the separation state of the launch vehicle and the test load as the terminal constraint, the flight load as the process constraint, and the launch angle, timing parameters, program angle parameters, and the mass and installation position of the counterweight as optimization parameters, the genetic optimization algorithm is used for optimization design and extreme pull-off trajectory simulation calculation.

[0061] Step 2: Based on the simulation results of the extreme deflection trajectory, the user analyzes the mission plan and decides whether to execute the test mission. If the mission plan results meet the requirements, the predicted trajectory data is sent to the telemetry vehicle and the external measurement vehicle as a prediction of the ground antenna pointing direction, and the corresponding counterweight is installed in the counterweight compartment.

[0062] Step 3: The assembled launch vehicle is hoisted onto the launch vehicle, and the parameters obtained from the trajectory planning are sent to the integrated launch vehicle unit and the launch and control vehicle through the integrated control unit.

[0063] Step 4: After the launch vehicle, telemetry vehicle, and launch control vehicle travel in formation to the launch point, the system is deployed and cables are laid and connected. The launch vehicle is placed in position according to the predetermined launch direction and awaits the launch process.

[0064] Step 5: After the external test vehicle reaches the designated location, the system will be deployed as planned and the signal search will begin.

[0065] Step 6: After entering the launch process, the hydraulic servo mechanism on the launch vehicle drives the launch pad to be erected and rotated to the predetermined launch angle and azimuth angle, and feeds the results back to the ground integrated control unit. The results are compared with the launch data parameters. After the requirements are met, the launch control vehicle begins to check the erection status performance of the launch vehicle, mainly checking the resistance values ​​of the engine, pyrotechnic batteries and timing pyrotechnics, as well as the electrical performance and system flow of other onboard equipment. After entering the launch process, the telemetry vehicle and the external measurement vehicle begin to receive and save telemetry information.

[0066] Step 7: After entering launch zero point, the launch control vehicle issues an ignition command, and the launch vehicle departs from orbit under the propulsion of the engine and enters the ascent phase; when the conditions for test payload separation are met, the launch platform issues a separation command, and the test payload is released from the constraints of the launch platform and enters the test flight state.

[0067] Step 8: After completing the flight test, the launch vehicle, telemetry vehicle, launch and control vehicle, and external measurement vehicle return to the technical base and transmit the test data to the ground integrated control unit via fiber optic cable. The test data is analyzed to generate an analysis report for user decision-making.

[0068] The flight test system includes a test payload, test platform, launch device, launch control equipment, ground telemetry equipment, and ground integrated control unit. All equipment is organically integrated with the vehicle-mounted platform to form a mobile rocket launch system. The test platform, mounted on the launch vehicle, consists of a rocket structural system (including a counterweight module), control system, electrical equipment, telemetry equipment, and rocket engine, employing a vehicle-mounted inclined hot launch method. The launch control equipment, mounted on the launch vehicle, performs pre-launch checks on the test platform using cables. After passing the tests, the launch process begins, and the rocket engine ignition command is issued at the set time. The rocket booster engines ignite, propelling the test platform along the launch device to accelerate off-orbit and climb. The control system then activates, outputting servo control commands in real time to achieve stable flight control of the test platform. After the rocket engine finishes firing, the test platform continues its inertial climb, achieving the flight trajectory and attitude required by the test payload. When conditions are met, a fairing jettison command is issued, followed by a payload separation command when separation conditions are met. The test payload completes its predetermined test mission until the flight mission ends.

[0069] Throughout the entire flight operation of the test platform, its telemetry equipment collects and transmits analog and digital signals in real time. The telemetry vehicle is located near the launch site and receives, stores, and processes the telemetry data before and after launch. The external measurement vehicle receives the telemetry parameters of the launch vehicle throughout the entire flight and assesses the health status of the test platform.

[0070] The test system employs a vehicle-mounted tilting hot-launch method, enabling self-launch with a simple launch process and low environmental requirements. The test platform utilizes a modular design, reducing coupling between systems. The launch platform provides universal mechanical interfaces for the test payload, which can be connected via adapters. The platform also provides at least five RS422 communication interfaces and a 28V power supply interface for signal transmission and power supply to the payload. The test platform can be divided into the following sections: fairing compartment, separation compartment, servo compartment, counterweight compartment, control compartment, solid rocket motor compartment, and tail fin assembly compartment.

[0071] The test load is installed inside the fairing, which has a split structure consisting of a head cover and a cone. Both the head cover and the cone are made of composite materials, and the head cover and the cone are axially connected and fixed together by bolts. The head cover houses a separation mechanism that provides multiple multi-voltage power supply signals and multiple serial communication signals to meet the diverse power supply, data transmission, and command reception needs of the load.

[0072] The separation compartment is equipped with retro-rockets for the separation of the fairing section from the rocket body and provides a certain relative separation velocity. The separation compartment has reserved space for installing counterweights when the test load mass is low, ensuring the rocket's center of gravity meets static stability requirements. The required counterweight installation mass and location are automatically output by the ground control system based on the user-inputted load compartment mass and mission requirements, eliminating the need for time-consuming and labor-intensive redesign and matching.

[0073] The servo bay houses the servo drive and servo controller, and four control wings can be connected to the outside of the missile body for flight attitude stabilization and ballistic control.

[0074] The ballast compartment is used solely for installing ballast, primarily to adjust the static stability of the launch vehicle and its flight speed and altitude during load release. The ballast consists of multiple high-density mass blocks that can be freely combined to meet different ballast mass requirements. An axial installation position is pre-reserved within the compartment, allowing for axial repositioning of the installation location.

[0075] The control cabin houses an integrated control unit, which integrates the onboard computer, inertial navigation equipment, satellite navigation equipment, control batteries, servo batteries, timing controller, and telemetry acquisition and transmission assembly. Multiple telemetry antennas are evenly distributed around the cabin's circumference for rocket-to-ground communication and data transmission. The integrated control unit integrates and merges onboard equipment and can be upgraded via an external data interface to meet diverse payload power supply, operation, data transmission, and timing control command requirements. Before launch, the ground-based integrated control unit sets the data parameters to enable multi-flight mission functionality.

[0076] The solid rocket motor nacelle consists of solid rocket motors, which provide flight propulsion. To meet the requirements of diverse test payloads and large-envelope flight environments, the solid rocket motors have a large energy margin, satisfying the requirements of high-altitude, high-speed flight conditions. If the test payload requires a low-altitude, low-speed flight environment, the ground control system manages energy according to the test mission requirements, automatically generating trapezoidal or S-shaped program angle commands to consume excess energy. The entire process is automated, improving analysis and calculation efficiency while reducing the possibility of data transmission errors, thus meeting the diverse needs of test payloads.

[0077] The tail fin assembly consists of four wing surfaces and a structural component, used to stabilize the rocket body.

[0078] The launch and control system adopts a front-end and back-end distributed control approach. The entire system consists of a front-end integrated adapter, a remote controller, and telemetry and control cables. The integrated adapter, located inside the launch vehicle, is the execution end of the telemetry and control mission. It connects to the rocket via a rocket-to-ground cable to complete communication between the rocket and the ground, measure rocket parameters, and control rocket ignition and launch. The remote controller, located inside the launch and control vehicle, is the mission management end of the launch and control system. It receives system status information sent by the front-end adapter in real time, processes and displays it, and issues operator commands to the front-end adapter. The front-end and back-end devices communicate with each other via telemetry and control cables.

[0079] The launch vehicle consists of a launch and control front-end integrated adapter, an electric actuator system, an electrical system, a turntable, a launch pad, an electric protective cover, an equipment compartment, a rocket securing and protection mechanism, a missile retrieval mechanism, a tractor unit, and a trailer chassis. Its functions are as follows:

[0080] The rocket is loaded for short-distance road transport, and the protective shield provides the rocket with protection from wind, rain, and sandstorms.

[0081] The vehicle is reliably supported by electric cylinders for the outriggers, which automatically level itself from left to right.

[0082] The launch pad is used to erect and rotate the rocket, providing the rocket with the specified firing angle.

[0083] Autonomous positioning and orientation;

[0084] Provide power to the power control system.

[0085] The telemetry vehicle and external measurement vehicle system mainly consists of an antenna feeder system, a telemetry receiving subsystem, a front-end data processing and display subsystem, a time and frequency subsystem, a software subsystem, a calibration subsystem, a self-testing subsystem, a monitoring subsystem, and a modular shelter. Its main functions are as follows:

[0086] It can simultaneously receive broadband, high-dynamic telemetry data stream signals from both LHCP and RHCP channels, and complete telemetry signal diffusing and synthesis processing.

[0087] It has the functions of receiving and demodulating PCM-FM, PCM-BPSK and PCM-QPSK telemetry signals;

[0088] It has GNSS time synchronization and positioning / orientation functions;

[0089] The Tianwei Feeder Subsystem has manual tracking, program tracking, automatic search, automatic tracking, memory tracking, and digitally guided tracking functions;

[0090] It has the function of generating and receiving IRIG-B time codes;

[0091] It has the functions of recording all telemetry data in real time, real-time and post-event data processing, and networked data transmission.

[0092] It has functions such as monitoring, setting, and status display of each extension unit, as well as real-time data display and external data transmission.

[0093] The system has baseband / RF closed-loop self-test, verification, and status testing functions.

[0094] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A generalized hypersonic flight test system, characterized by, Includes payload system, ground system, and test launch platform. The ground system is used for flight test support, providing test environment simulation, flight program injection, system transfer, parameter setting, launch platform erection, launch control, and data retrieval for the launch platform. It includes the ground control unit, launch vehicle, telemetry and control vehicle, telemetry vehicle, and external measurement vehicle. The ground control unit is the central node of the entire test system, used for mission planning, parameter command issuance, and data collection and analysis. The launch vehicle is equipped with a telemetry, launch and control front-end and a carrier. The telemetry, launch and control front-end is used to execute the command signals transmitted from the telemetry, launch and control vehicle. The carrier includes a carrier platform and a test payload. The test payload is installed in the fairing of the test platform. The test platform provides the test payload with the flight environment, power supply and communication conditions. Telemetry vehicles and external measurement vehicles are used to receive telemetry data before and during flight; The testing system includes mission planning and flight testing; During mission planning, the mission planning unit built into the integrated control computer is used to automatically plan the mission. The mission planning unit has built-in aerodynamic parameters, mass parameters, load parameters, dynamic performance parameters and control program parameters of the launch vehicle. The genetic optimization algorithm is used to optimize the design of the counterweight mass parameters, launch parameters and timing parameters. The flight performance under standard and extreme pull conditions is used as the index constraint to generate the optimal flight trajectory that meets the working conditions of the test load. After completing flight performance calculations on the ground control aircraft, the structural strength of the launch vehicle is verified, the flight test mission planning is completed, and decisions are made regarding the flight test. After confirming the execution of the flight mission, a counterweight is installed on the test launch platform, and the parameters output by the mission planning unit are sent to the launch vehicle and the telemetry and control vehicle, while the standard flight trajectory is sent to the telemetry vehicle and the external measurement vehicle. After completing the flight test preparations, the launch vehicle, telemetry vehicle, and launch control vehicle traveled in formation to the launch site. After the launch vehicle was positioned according to the predetermined launch azimuth angle, the launch vehicle was erected to the designated launch angle. After entering the launch process, the launch vehicle was tested and launched, and the ignition and takeoff command was issued at the predetermined time. The launch vehicle was driven off the orbit by the rocket engine and flew according to the predetermined sequence. After meeting the payload working conditions, the test payload was separated and autonomously flown. After entering the launch process, the telemetry vehicle and the external measurement vehicle track the launch vehicle and test payload according to the predetermined trajectory, and receive and store telemetry data; After the flight test is completed, the test mission is automatically analyzed by collecting telemetry data and launch control data to generate a mission report for user decision-making.

2. A universal hypersonic flight test system according to claim 1, wherein The payload system is the core of the flight test system, specifically for hypersonic test vehicles.

3. A generalized hypersonic flight test system according to claim 1, wherein The test launch platform provides the initial working environment for the payload. After the payload reaches the working environment, the payload separates from the launch vehicle and completes the subsequent flight mission.

4. A generalized hypersonic flight test system according to claim 1, wherein The launch platform includes a steering system and a telemetry system. The steering system is used for attitude control of the launch platform, and the telemetry system is used for acquiring test data and monitoring its status.

5. A generalized hypersonic flight test system according to claim 1, wherein The ground control unit is used to combine the test mission instructions issued by the user with the capabilities of the carrier platform to perform mission evaluation, performance prediction, parameter design and configuration, receive telemetry signals, test data and issue control instructions.

6. A generalized hypersonic flight test system according to claim 1, wherein Users transmit flight conditions, mass characteristics, and power supply requirements of the test payload to the ground control unit, which then automatically performs mission planning and performance simulation analysis based on the capabilities of the launch platform.

7. A generalized hypersonic flight test system as in claim 1, wherein A counterweight position is reserved in the counterweight compartment of the launch platform to cope with the release mission of the payload under different flight altitude, flight speed and attitude conditions. During mission planning, the flight conditions, mass characteristics and performance parameters of the test payload and the launch platform are used as inputs, and the counterweight mass and installation position on the launch platform are used as output parameters. The optimization design is automatically performed using optimization algorithms such as genetic algorithms to ensure that the counterweight mass is minimized and the control system rudder usage is minimized while meeting the payload release conditions and flight load conditions.

8. A generalized hypersonic flight test system according to claim 1, wherein After the ground control unit completes the mission evaluation, it will provide feedback on the installation location, weight, and parameter results of the counterweight, and generate a report on the mission evaluation, including flight performance simulation and power analysis, for user decision-making.

9. A generalized hypersonic flight test system as in claim 1, wherein, If the flight mission is deemed feasible after evaluation, the corresponding counterweights will be installed in the counterweight compartment, the payload will be placed in the fairing, and the parameters will be loaded into the integrated control system of the launch platform via the ground integrated control unit to complete the mission planning.

10. A generalized hypersonic flight test system as in claim 1, wherein, After the ground support system transports the launch vehicle to the launch site, the launch vehicle is erected in position according to the firing direction and launch angle specified in the parameters and awaits the launch command. The telemetry and control vehicle is placed outside the safety zone to the side of the launch vehicle and is used to conduct system testing and launch control of the launch vehicle. The telemetry vehicle is placed outside the safety zone of the launch site and arranged to the side along the firing direction. It is used to receive telemetry information of the launch vehicle and payload issued by the launch vehicle on the ground and during the takeoff phase. The external telemetry vehicle is placed between the launch point and the landing point, outside the airway safety zone, and is used to receive telemetry information of the launch vehicle and payload in the phase after takeoff.

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