A method for verifying the function and performance of an air valve suitable for a troposphere manned airship

Abstract

The application belongs to the technical field of flight test, and discloses a method for verifying the function and performance of an air valve of a stratosphere manned airship, which is characterized by unified verification requirements formed by standardizing the flight test procedure and the flight test method. The application improves the flight test efficiency and quality of the manned airship.

Description

Technical Field

[0001] This invention belongs to the field of flight test technology, specifically relating to a flight test method for verifying the functional performance of the air valve of a tropospheric manned airship applicable to FAA P-8110-2. Background Technology

[0002] The present invention aims to propose a test flight method for verifying the functional performance of the air valve of a tropospheric manned airship. Currently, there is a need to achieve repeatable and standardized test flight requirements for airships, and to standardize the test flight procedures and methods to form unified verification requirements, thereby improving the efficiency and quality of manned airship test flights.

[0003] The Civil Aviation Administration of China (CAAC) issued the type certification for the airship (AC-21-AA-2009-09R1), which adopted FAA P-8110-2 airship design guidelines, specifically clauses 4.44(b) and 6.1(d), which stipulate the functional performance verification of air valves. The guidelines explicitly require that the airship must have at least one air valve to release air from each gasbag: this valve can be installed inside the gasbag or connected to it via suitable tubing; the valve must be operable manually and automatically, operable at all achievable airspeeds under appropriate pressure settings, and reliably open and close; the valve must have sufficient capacity to allow the airship to ascend below its pressure altitude at the maximum design climb rate without exceeding 1.15 times the maximum operating pressure of the helium gas; and each installed device must function normally after installation. Based on these requirements, this invention clarifies the flight test conditions and methods for verifying the functional performance of the air valves and provides qualification criteria. Summary of the Invention

[0004] This invention provides a flight test method for verifying the functional performance of air valves in tropospheric manned airships, thereby improving the efficiency and quality of manned airship flight tests.

[0005] The technical solution of this invention is implemented as follows: In a first aspect, the present invention provides a method for verifying the functional performance of an air valve on a tropospheric manned airship, comprising the following steps: Step 1: Before the test flight, complete the basic functional verification of the air valve's performance on the ground; Step 2: Set the working mode of the airbag pressure system to automatic, take off vectoring according to the conventional flight procedure, and after reaching a certain safe altitude, manipulate the thrust vector angle to turn from the takeoff thrust vector angle to 0°, and at the same time pull the stick to make the airship enter the climb state. Step 3: After climbing to a certain height, slowly pull the lever to a small and safe rate of ascent and hold it for a certain period of time. Gradually increase the throttle to the maximum continuous power and hold the throttle. Observe whether the airbag pressure is within the normal range. Step 4: Slowly pull back on the stick to increase the rate of climb. When the rate of climb reaches its maximum, maintain the rate of climb for a certain period of time using the elevator. Observe whether the airbag pressure can be maintained below 1.15 times the maximum operating pressure. Record the vertical speed at this time and recover to level flight. Step 5: Slowly push the stick to a small and safe glide rate and maintain it. Slowly increase the engine throttle to the maximum continuous power. When the glide rate reaches the maximum, maintain the glide rate for a certain period of time using the elevator. Observe whether the airbag pressure can be maintained above the minimum operating pressure. Record the vertical speed at this time and recover to level flight. Step 6: Repeat the test in the opposite direction; Step 7: After the test flight, compare the test flight data with the preset indicators to evaluate the reliability of the air valve's functional performance.

[0006] As a further technical solution of the present invention, it also includes an optimization and improvement step: if there is an abnormal working condition during the first to sixth steps, optimization and improvement suggestions are proposed for it, and then the above steps are repeated until the qualification criteria are met.

[0007] As a further technical solution of the present invention: the qualification criterion is specifically: during the entire flight process, when the airship flies at the maximum climb rate below the pressure altitude, the air valve can maintain the airbag pressure at less than 1.15 times the maximum operating pressure; the airbag pressure system equipment functions normally during the test.

[0008] As a further technical solution of the present invention: the basic function verification includes: air valve switching function test and air valve performance test when the airship is anchored.

[0009] As a further technical solution of the present invention: in the second step, the safety field height is 30m.

[0010] As a further technical solution of the present invention: in the third step, the climb height is 100m; the rod is slowly pulled to a smaller and safer climbing rate of 2m / s.

[0011] As a further technical solution of the present invention: in the fourth step, the climbing rate reaches a maximum range of 7m / s to 9m / s; the climbing rate is maintained for a certain period of time of 20s; the maximum operating pressure is 1.15 times that of 630Pa.

[0012] As a further technical solution of the present invention: in the fifth step, the smaller and safer descent rate is 2m / s; the descent rate reaches a maximum range of 4m / s to 6m / s; the descent rate is maintained for a certain period of time of 20s; and the minimum operating pressure is 200Pa.

[0013] In a second aspect, the present invention provides an electronic device comprising: a processor and a memory storing a computer program, wherein the above-described flight test method is implemented when the processor runs the computer program.

[0014] Thirdly, the present invention provides a computer storage medium storing a computer program, which, when executed by a processor, implements the above-described flight test method.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. This invention fills the gap in flight test methods for verifying the functional performance of air valves in tropospheric manned airships, and improves the efficiency and quality of manned airship flight tests.

[0016] 2. This invention fills the gap in the test flight method for verifying the functional performance of air valves on tropospheric manned airships, realizes a repeatable and standardized test flight plan, standardizes the test flight procedures and methods, forms unified verification requirements, and improves the test flight efficiency and quality of verifying the functional performance of air valves on tropospheric manned airships.

[0017] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the implementation process for verifying the functional performance of the air valve on the tropospheric manned airship according to the present invention. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below with reference to the accompanying drawings.

[0020] In the accompanying drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present invention.

[0021] The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0022] The following is in conjunction with the appendix Figure 1 The embodiments of the present invention will be described in detail below.

[0023] Example 1 The present invention provides the following flight test process for verifying the functional performance of an air valve on a manned airship: 1) Before the test flight, complete the basic functional verification of the air valve's function and performance on the ground, such as the air valve switching function test and air valve performance test when the airship is in the anchored state; 2) Set the working mode of the airbag pressure system to automatic, take off according to the conventional flight procedure, and after reaching an altitude of 30m, manipulate the thrust vector angle to change from the takeoff thrust vector angle to 0°, and at the same time pull the stick to make the airship enter the climb state. 3) After climbing to a height of 100m~150m, slowly pull the lever to a climbing rate of more than 2m / s and hold for 10s. Gradually increase the throttle to the maximum continuous power and hold the throttle. Observe whether the airbag pressure is within the normal range. 4) Slowly pull back on the stick to increase the rate of climb. When the rate of climb reaches its maximum (7m / s to 9m / s), maintain the rate of climb for 20 seconds using the elevator. Observe whether the airbag pressure can be maintained below 1.15 times the maximum operating pressure (630Pa). Record the vertical speed at this time and recover to level flight. 5) Slowly push the stick to a glide rate of about 2m / s and hold it. Slowly increase the engine throttle to the maximum continuous power. When the glide rate reaches the maximum (4m / s to 6m / s), maintain the glide rate for 20s using the elevator. Observe whether the airbag pressure can be maintained above the minimum operating pressure (200Pa). Record the vertical speed at this time and recover to level flight. 6) Repeat the test in the opposite course; 7) After the test flight, the reliability of the air valve function performance was evaluated by comparing the test flight data with the preset indicators. The pass criterion was that during the entire flight, when the airship was flying at the maximum rate of climb below the pressure altitude, the air valve could maintain the airbag pressure at less than 1.15 times the maximum operating pressure; the airbag pressure system equipment functioned normally during the test. 8) The test flight results meet the qualification criteria, and the test flight is completed.

[0024] Example 2 This invention provides a method for verifying the functional performance of a tropospheric manned air valve applicable to FAA P-8110-2 during flight testing. The method comprises the following steps: Step 1: Before the test flight, complete the basic functional verification of the air valve's function and performance on the ground, such as the air valve opening and closing function test and air valve performance test when the airship is in an anchored state. Step 2: Set the working mode of the airbag pressure system to automatic, take off according to the conventional flight procedure, and after reaching a certain safe altitude (such as 30m), manipulate the thrust vector angle to turn from the takeoff thrust vector angle to 0°, and at the same time pull the stick to make the airship enter the climb state. Step 3: After climbing to a certain height (e.g., 100m), slowly pull the lever to a small and safe rate of ascent (e.g., 2m / s) and maintain it for a certain period of time. Gradually increase the throttle to the maximum continuous power and maintain the throttle. Observe whether the airbag pressure is within the normal range. Step 4: Slowly pull back on the stick to increase the rate of climb. When the rate of climb reaches its maximum (e.g., 7m / s to 9m / s), maintain the rate of climb for a certain period of time (e.g., 20s) using the elevator. Observe whether the airbag pressure can be maintained below 1.15 times the maximum operating pressure (e.g., 630Pa). Record the vertical speed at this time and recover to level flight. Step 5: Slowly push the stick to a small and safe glide rate (e.g., 2m / s) and maintain it. Slowly increase the engine throttle to the maximum continuous power. When the glide rate reaches the maximum (e.g., 4m / s to 6m / s), maintain the glide rate for a certain period of time (e.g., 20s) using the elevator. Observe whether the airbag pressure can be maintained above the minimum operating pressure (e.g., 200Pa). Record the vertical speed at this time and recover to level flight. Step 6: Repeat the test in the opposite direction; Step 7: If any abnormal conditions occur during the above process, suggestions for optimization and improvement shall be made, and the above steps shall be repeated until the qualification criteria are met, that is, during the entire flight, when the airship flies at the maximum rate of climb below the pressure altitude, the air valve can keep the airbag pressure below 1.15 times the maximum operating pressure; the airbag pressure system equipment functions normally during the test.

[0025] Example 3 This invention provides an electronic device, including: a processor and a memory storing a computer program; in practical applications, there may be one or more processors; there may be one or more memories. When the processor runs the computer program, the flight test method applied to the above-mentioned electronic device is implemented.

[0026] The memory can be volatile or non-volatile, or both. Non-volatile memory can be read-only memory (ROM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), electrically erasable programmable read-only memory (EEPROM), ferromagnetic random access memory (FRAM), flash memory, magnetic surface memory, optical disc, or compact disc read-only memory (CD-ROM); magnetic surface memory can be disk storage or magnetic tape storage. Volatile memory can be random access memory (RAM), used as an external cache. By way of example, but not limitation, many forms of RAM are available, such as Static Random Access Memory (SRAM), Synchronous Static Random Access Memory (SSRAM), Dynamic Random Access Memory (DRAM), Synchronous Dynamic Random Access Memory (SDRAM), Double Data Rate Synchronous Dynamic Random Access Memory (DDRSDRAM), Enhanced Synchronous Dynamic Random Access Memory (ESDRAM), SyncLink Dynamic Random Access Memory (SLDRAM), and Direct Rambus Random Access Memory (DRRAM).

[0027] The memory of this invention is used to store various types of data to support the operation of the electronic device. Examples of such data include: any computer programs used to operate on the electronic device, such as operating systems and applications; contact data; phonebook data; messages; pictures; videos, etc. The operating system includes various system programs, such as a framework layer, core library layer, driver layer, etc., used to implement various basic services and handle hardware-based tasks. Applications can include various applications, such as media players, browsers, etc., used to implement various application services. Here, the program implementing the method of the embodiments of this invention can be included in the application.

[0028] Example 4 This invention provides a computer storage medium storing a computer program. The computer storage medium can be a magnetic random access memory (FRAM), a read-only memory (ROM), a programmable read-only memory (PROM), an erasable programmable read-only memory (EPROM), an electrically erasable programmable read-only memory (EEPROM), a flash memory, a magnetic surface memory, an optical disc, or a compact disc read-only memory (CD-ROM), etc.; it can also be various devices including one or any combination of the above-mentioned memories, such as mobile phones, computers, tablet devices, personal digital assistants, etc. When the computer program stored in the computer storage medium is executed by a processor, it implements the flight test method applied to the aforementioned electronic device.

[0029] Thus, the objective of this invention has been achieved.

[0030] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for verifying the functional performance of an air valve on a tropospheric manned airship, characterized in that, Includes the following steps: Step 1: Before the test flight, complete the basic functional verification of the air valve's performance on the ground; Step 2: Set the working mode of the airbag pressure system to automatic, take off vectoring according to the conventional flight procedure, and after reaching a certain safe altitude, manipulate the thrust vector angle to turn from the takeoff thrust vector angle to 0°, and at the same time pull the stick to make the airship enter the climb state. Step 3: After climbing to a certain height, slowly pull the lever to a small and safe rate of ascent and hold it for a certain period of time. Gradually increase the throttle to the maximum continuous power and hold the throttle. Observe whether the airbag pressure is within the normal range. Step 4: Slowly pull back on the stick to increase the rate of climb. When the rate of climb reaches its maximum, maintain the rate of climb for a certain period of time using the elevator. Observe whether the airbag pressure can be maintained below 1.15 times the maximum operating pressure. Record the vertical speed at this time and recover to level flight. Step 5: Slowly push the stick to a small and safe glide rate and maintain it. Slowly increase the engine throttle to the maximum continuous power. When the glide rate reaches the maximum, maintain the glide rate for a certain period of time using the elevator. Observe whether the airbag pressure can be maintained above the minimum operating pressure. Record the vertical speed at this time and recover to level flight. Step 6: Repeat the test in the opposite direction; Step 7: After the test flight, compare the test flight data with the preset indicators to evaluate the reliability of the air valve's functional performance.

2. The method for verifying the functional performance of air valves in tropospheric manned airships according to claim 1, characterized in that, It also includes optimization and improvement steps: if there are any abnormal working conditions during the first to sixth steps, optimization and improvement suggestions are proposed, and then the above steps are repeated until the qualification criteria are met.

3. The method for verifying the functional performance of air valves in tropospheric manned airships according to claim 2, characterized in that, The qualification criteria are as follows: during the entire flight, when the airship is flying at the maximum rate of climb below the pressure altitude, the air valve can maintain the airbag pressure at less than 1.15 times the maximum operating pressure; the airbag pressure system equipment functions normally during the test.

4. The method for verifying the functional performance of air valves in tropospheric manned airships according to claim 1, characterized in that, The basic functional verification includes: testing the air valve switching function and air valve performance when the airship is anchored.

5. The method for verifying the functional performance of air valves in tropospheric manned airships according to claim 1, characterized in that, In the second step, the safe field height is 30m.

6. The method for verifying the functional performance of air valves in tropospheric manned airships according to claim 1, characterized in that, In the third step, climb to a certain height of 100m; slowly pull the lever to a smaller and safer climbing rate of 2m / s.

7. The method for verifying the functional performance of air valves in tropospheric manned airships according to claim 1, characterized in that, In the fourth step, the climb rate reaches a maximum range of 7m / s to 9m / s; the climb rate is maintained for a certain period of 20s; the maximum operating pressure is 1.15 times the maximum pressure, which is 630Pa.

8. The method for verifying the functional performance of air valves in tropospheric manned airships according to claim 1, characterized in that, In the fifth step, the smaller and safer descent rate is 2m / s; the maximum descent rate is within the range of 4m / s to 6m / s; the descent rate is maintained for a certain period of 20s; and the minimum operating pressure is 200Pa.

9. An electronic device, characterized in that, include: The processor and the memory storing the computer program implement the flight test method according to any one of claims 1 to 8 when the processor runs the computer program.

10. A computer storage medium, characterized in that, The system contains a computer program that, when executed by a processor, implements the flight test method according to any one of claims 1 to 8.

Images