CN217673295U - Testing device for parachute opening device of full-automatic parachute - Google Patents
Testing device for parachute opening device of full-automatic parachute Download PDFInfo
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- CN217673295U CN217673295U CN202221840821.2U CN202221840821U CN217673295U CN 217673295 U CN217673295 U CN 217673295U CN 202221840821 U CN202221840821 U CN 202221840821U CN 217673295 U CN217673295 U CN 217673295U
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Abstract
The utility model discloses a testing device of a parachute opening device of a full-automatic parachute, which comprises an airdrop testing platform, a pitot tube speed measuring device, a front hoisting joint device, a camera bracket, a rear hoisting joint device, a parachute device and a data acquisition device; the airdrop test platform comprises a cylindrical platform body; the device comprises a parachute device and a speed measuring device, wherein the parachute device comprises a launching tube, and a parachute pack, a bracket and a gas ejection device are arranged in the launching tube; the platform body rear end still be equipped with back hoist and mount piecing devices, back hoist and mount piecing devices include installing support, back hoisting point joint, installing support bottom fix in the platform body outside, back hoisting point joint locate the installing support top. The utility model can carry out ejection test according to the set time, can simulate the real parachute opening airspeed condition, and is more in line with the actual parachute opening working condition; the testing device can be repeatedly used and is convenient to install.
Description
Technical Field
The utility model relates to a parachute opening test equipment technical field specifically is a testing arrangement of full quick-witted parachute opening device.
Background
The full-aircraft parachute is a complete-aircraft parachute escape system controlled by a pilot, and is a safety device for rescuing passengers and airplanes under emergency conditions that any other emergency program cannot guarantee safety. The parachute kit is usually stored at the rear part of a cabin partition of the airplane, and the parachute is opened under the control of a pilot, so that the whole airplane can land safely. Full-aircraft parachutes were originally developed for ultra-light and experimental aircraft, and as technology developed, full-aircraft parachute products have become popular with many ultra-light, experimental aircraft and light sports aircraft in europe and america.
The main test methods for parachute opening at present are as follows: high-altitude parachute throwing test, ground parachute opening test, ground ballistic parachute opening test and the like. However, the above test conditions cannot completely verify the whole process from activation to parachute opening and attitude adjustment of the aircraft parachute in a real incoming flow environment. Therefore, for the research of the parachute opening test method and the test device of the full-aircraft parachute, the parachute opening process of the aircraft is simulated as much as possible, and the real situation is restored.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a testing arrangement of full quick-witted parachute opening device simulates the parachute opening process of full quick-witted parachute under the flight condition, verifies the function of the full quick-witted parachute opening system of aircraft, makes the full quick-witted parachute opening test more be close true parachute opening process.
In order to achieve the above object, the utility model provides a following technical scheme:
a testing device of a full-aircraft parachute opening device comprises an airdrop testing platform, a pitot tube speed measuring device, a front hoisting connector device, a camera support, a rear hoisting connector device, a parachute device and a data acquisition device; the airdrop test platform comprises a cylindrical platform body; the pitot tube speed measuring device comprises a pitot tube and a sensor, and the pitot tube is fixed at the front end of the platform body through a bracket; the front hoisting joint device comprises front hoisting point joints respectively positioned at two sides of the front end of the platform body; the middle part of the platform body is provided with an equipment cabin which is sunken inwards, and the camera support is fixed on the outer side of a hatch of the equipment cabin; the rear end of the platform body is provided with an inwards-concave parachute cabin, the parachute device is arranged in the parachute cabin and comprises a launching tube, and a parachute bag, a bracket and a gas ejection device are arranged in the launching tube; the rear end of the platform body is also provided with a rear hoisting joint device, the rear hoisting joint device comprises a mounting bracket and a rear hoisting point joint, the bottom of the mounting bracket is fixed on the outer side of the platform body, and the rear hoisting point joint is arranged at the top end of the mounting bracket; the data acquisition device comprises a DAS data acquisition unit, the DAS data acquisition unit is arranged in the equipment chamber, and the DAS data acquisition unit is electrically connected with the pitot tube speed measuring device and the gas ejection device.
As the utility model discloses preferred scheme, air-drop test platform rear end tip be equipped with inside sunken reserve parachute cabin, reserve parachute cabin in be equipped with emergent parachute device.
As the utility model discloses preferred scheme, the sensor include acceleration sensor, GPS recorder, pressure sensor, differential pressure sensor.
As the utility model discloses preferred scheme, preceding hoist and mount joint device including the cylinder water injection cabin of locating platform body front end both sides, the water injection cabin on be equipped with preceding hoisting point respectively and connect.
As the utility model discloses preferred scheme, the installing support be the tripod, the tripod top be equipped with back hoisting point and connect, force sensor be connected with DAS data acquisition unit electricity.
As the utility model discloses preferred scheme, DAS data acquisition unit fix in camera mount below, DAS data acquisition unit position press close to air-drop test platform focus position.
The platform main body of the airdrop test platform is formed by welding steel pipes, the test platform is designed according to the gravity center position, the front lifting point position, the rear lifting point position and the launching tube position of a certain airplane, and the relative positions of the gravity center on the test platform, the front lifting point, the rear lifting point and the launching tube are consistent with the certain airplane; the launching tube is provided with a parachute system assembly, comprises a parachute pack, a bracket and a gas generator (ejection device), and is used for simulating the process of ejecting the parachute by an airplane; front hanging point joints are arranged at two ends of the water injection cabin and used for connecting a front hanging strip and a rear hanging point joint and used for installing a rear hanging point release assembly of the parachute; the front end of the airdrop test platform is reserved with a mounting position of a pitot tube, a camera bracket is reserved in the middle, and the observation direction is the visual angle of the opened parachute; DAS data acquisition unit installs in camera mount below space, presses close to the focus position, and aircraft actual weight has been considered when the design to the accessible adds suitable water yield for the water injection cabin and adjusts and reach the maximum weight of aircraft, and above design makes this scheme device of adoption carry out the air-drop and launch the parachute-opening test and more be close to true condition.
The system is provided with a DAS data acquisition unit and integrates a plurality of sensors, wherein acceleration data are acquired by an Adafruit ADXL345 acceleration sensor, and the acquisition frequency is about 40Hz; the GPS system consists of a GPS module of a SparkFun Venus GPS recorder (with an SMA connector), a coaxial jumper connected to the shell from the module and a special SD card recorder for storing data; the method comprises the following steps of measuring pressure by using an NXP MPXA6115AC7U absolute pressure sensor and a Honeywell SSCDRN 001PDAA5 differential pressure sensor, wherein the sensors and a pitot tube jointly form a pitot tube speed measuring device; the force sensor measures the limit load released by an inner loop of the rear sling by using a Transducer Techniques CLP-12.5K force sensor, the range of the force sensor is 12500lbs, the force sensor is installed at the position below a joint of a rear lifting point of the fuselage, and the force sensor are both installed on a mounting bracket of the rear lifting point of the simulated fuselage.
When the scheme is used for testing, the carrier aircraft is carried into the air and is thrown into the air at a proper position, and after the test platform is thrown, an airborne electronic timing program can excite an ejection device in the parachute assembly after 9 seconds of delay; and the airborne electronic timing program can excite an independent ejection device in the parachute for emergency deceleration after 30 seconds of delay, and eject a parachute pack, so that the platform is grounded at a relatively low speed, and the risk of the test is reduced.
Compared with the prior art, the beneficial effects of the utility model are that:
the ejection test can be carried out according to the set time, the real parachute opening airspeed condition can be simulated, and the practical parachute opening working condition is better met; the testing device can be repeatedly used and is convenient to install.
Drawings
Fig. 1 is a schematic structural diagram of the platform body of the present invention.
Fig. 2 is a schematic structural diagram of the present invention.
Fig. 3 is a schematic structural diagram of the camera support of the present invention.
Fig. 4 is a schematic diagram of a circuit structure according to the present invention.
In the figure: 1. platform body 2, pitot tube 3, support 4, preceding hoisting point connect
5. Equipment cabin 6, camera support 7, parachute cabin 8 and launching tube
9. Installing support 10, back hoisting point joint 11, DAS data acquisition unit
12. Standby parachute bay 13, emergency parachute device 14 and acceleration sensor
15. GPS recorder 16, pressure sensor 17, differential pressure sensor
18. And a water injection cabin.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, rather than all embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative work belong to the scope of the present invention based on the embodiments of the present invention.
It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present, that when an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present, and that the terms "vertical", "horizontal", "left", "right" and the like are used herein for descriptive purposes only.
Referring to fig. 1-4, the present invention provides a technical solution:
a testing device for a parachute opening device of a full-aircraft parachute comprises an airdrop testing platform, a pitot tube speed measuring device, a front hoisting connector device, a camera support, a rear hoisting connector device, the parachute device and a data acquisition device; the airdrop test platform comprises a cylindrical platform body 1; the pitot tube speed measuring device comprises a pitot tube 2 and a sensor, wherein the pitot tube 2 is fixed at the front end of the platform body 1 through a bracket 3; the front hoisting joint device comprises front hoisting point joints 4 which are respectively positioned at two sides of the front end of the platform body 1; an equipment cabin 5 which is sunken inwards is arranged in the middle of the platform body 1, and a camera support 6 is fixed on the outer side of a hatch of the equipment cabin 5; an inwards-sunken parachute cabin 7 is arranged at the rear end of the platform body 1, a parachute device is arranged in the parachute cabin 7 and comprises a launching tube 8, and a parachute bag, a bracket and a gas ejection device are arranged in the launching tube 8; the rear end of the platform body 1 is also provided with a rear hoisting connector device, the rear hoisting connector device comprises a mounting bracket 9 and a rear hoisting point connector 10, the bottom of the mounting bracket 9 is fixed on the outer side of the platform body 1, and the rear hoisting point connector 10 is arranged at the top end of the mounting bracket 9; the data acquisition device comprises a DAS data acquisition unit 11, the DAS data acquisition unit 11 is arranged in the equipment cabin 5, and the DAS data acquisition unit 11 is electrically connected with the pitot tube speed measuring device and the gas ejection device.
An inwards-sunken standby umbrella cabin 12 is arranged at the rear end of a platform body 1 of the airdrop test platform, and an emergency speed-reducing umbrella device 13 is arranged in the standby umbrella cabin 12.
The sensors include an acceleration sensor 14, a GPS recorder 15, a pressure sensor 16, and a differential pressure sensor 17.
The front hoisting joint device comprises cylindrical water injection cabins 18 arranged at two sides of the front end of the platform body 1, and front hoisting point joints 4 are respectively arranged on the water injection cabins 18.
The mounting bracket 9 is a tripod, the top end of the tripod is provided with a rear hoisting point joint 10 and a force sensor, and the force sensor is electrically connected with the DAS data acquisition unit.
DAS data acquisition unit 11 is fixed in camera mount 6 below, and DAS data acquisition unit 11 position is close to air-drop test platform focus position.
The utility model discloses work flow: after the air-drop test platform is installed, the air-drop test platform is hoisted by adopting a front hoisting belt and a rear hoisting belt and is carried to a designated position by a carrier aircraft to be dropped in the air;
an airplane parachute system assembly is installed in a launching tube 8 of an airdrop test platform and comprises a parachute bag, a bracket and a gas ejection device, wherein the parachute bag is in a compressed packaging mode and is placed in the launching tube 8 together with the gas ejection device, a front hanging strip is connected with a front hanging point joint 4, a rear hanging strip is connected with a rear hanging point joint 10, and when the airdrop test platform is put in, an airborne electronic timing program can excite the gas ejection device installed in the launching tube 8 and eject the parachute bag to be opened after 9 seconds of delay;
a small emergency parachute device 13 is installed at the rear part of the airdrop test platform, an airborne electronic timing program can excite an independent ejection device in the emergency parachute device 13 after 30 seconds of delay, an emergency deceleration parachute pack is ejected, and an emergency deceleration parachute is opened to ensure that the airdrop test platform is grounded at a relatively low speed and the risk of a test is reduced;
the DAS data acquisition unit 11 acquires and records data of each sensor during the release process.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides a testing arrangement of full quick-witted parachute-opening device which characterized in that: the device comprises an airdrop test platform, a pitot tube speed measuring device, a front hoisting connector device, a camera bracket, a rear hoisting connector device, a parachute device and a data acquisition device;
the airdrop test platform comprises a cylindrical platform body;
the pitot tube speed measuring device comprises a pitot tube and a sensor, and the pitot tube is fixed at the front end of the platform body through a bracket;
the front hoisting joint device comprises front hoisting point joints respectively positioned at two sides of the front end of the platform body;
the middle part of the platform body is provided with an equipment cabin which is sunken inwards, and the camera support is fixed on the outer side of a hatch of the equipment cabin;
the rear end of the platform body is provided with an inwards-concave parachute cabin, the parachute device is arranged in the parachute cabin and comprises a launching tube, and a parachute bag, a bracket and a gas ejection device are arranged in the launching tube;
the rear end of the platform body is also provided with a rear hoisting joint device, the rear hoisting joint device comprises a mounting bracket and a rear hoisting point joint, the bottom of the mounting bracket is fixed on the outer side of the platform body, and the rear hoisting point joint is arranged at the top end of the mounting bracket;
the data acquisition device comprises a DAS data acquisition unit, the DAS data acquisition unit is arranged in the equipment compartment, and the DAS data acquisition unit is electrically connected with the pitot tube speed measuring device and the gas ejection device.
2. The testing device for the parachute opening device of the full-aircraft parachute according to claim 1, wherein: the back end of the airdrop test platform is provided with an inward-sunken standby umbrella cabin, and an emergency speed reducing umbrella device is arranged in the standby umbrella cabin.
3. The testing device for the parachute opening device of the full-aircraft parachute according to claim 1, wherein: the sensor comprises an acceleration sensor, a GPS recorder, a pressure sensor and a differential pressure sensor.
4. The test device for the parachute opening device of the full-aircraft parachute according to claim 1, wherein: the front hoisting joint device comprises cylindrical water injection cabins arranged on two sides of the front end of the platform body, and front hoisting point joints are respectively arranged on the water injection cabins.
5. The testing device for the parachute opening device of the full-aircraft parachute according to claim 1, wherein: the mounting bracket is a tripod, the top end of the tripod is provided with a rear lifting point joint and a force sensor, and the force sensor is electrically connected with the DAS data acquisition unit.
6. The testing device for the parachute opening device of the full-aircraft parachute according to claim 1, wherein: the DAS data acquisition unit is fixed below the camera support, and the DAS data acquisition unit is close to the gravity center of the air-drop test platform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221840821.2U CN217673295U (en) | 2022-07-14 | 2022-07-14 | Testing device for parachute opening device of full-automatic parachute |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221840821.2U CN217673295U (en) | 2022-07-14 | 2022-07-14 | Testing device for parachute opening device of full-automatic parachute |
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| Publication Number | Publication Date |
|---|---|
| CN217673295U true CN217673295U (en) | 2022-10-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221840821.2U Active CN217673295U (en) | 2022-07-14 | 2022-07-14 | Testing device for parachute opening device of full-automatic parachute |
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| Country | Link |
|---|---|
| CN (1) | CN217673295U (en) |
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2022
- 2022-07-14 CN CN202221840821.2U patent/CN217673295U/en active Active
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