CN110940531B - Device and method for researching unlocking separation time sequence and reliability of aircraft cabin - Google Patents
Device and method for researching unlocking separation time sequence and reliability of aircraft cabin Download PDFInfo
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- CN110940531B CN110940531B CN201911209442.6A CN201911209442A CN110940531B CN 110940531 B CN110940531 B CN 110940531B CN 201911209442 A CN201911209442 A CN 201911209442A CN 110940531 B CN110940531 B CN 110940531B
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- G01M17/00—Testing of vehicles
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Abstract
The invention provides a test device and a method for researching an unlocking separation time sequence and separation reliability of an aircraft cabin, wherein the device comprises a base, an electromagnetic hook, a locking screw and a clamping tongue upright post; the upper part of the latch upright post is provided with a spring latch device, and the spring latch device comprises a latch, a compression spring and a screw rod; in an initial state, the compression spring pushes the clamping tongue to be exposed, and at the moment, the exposed upper surface of the clamping tongue is a horizontal plane, and the lower surface of the clamping tongue is an inclined plane; after the electromagnetic hanging elastic hook is released, the cabin B section is separated from the cabin A section under the action of the spring assembly, the cabin B section firstly contacts the lower surface of the clamping tongue and pushes the clamping tongue to rotate in the axial direction of the pin, the cabin B section continuously rises and is separated from the clamping tongue, the clamping tongue returns to the initial state, and when the cabin B section falls from the highest point, the cabin B section falls on the upper surface of the clamping tongue to finish the falling recovery of the cabin B section. According to the invention, the electromagnetic hanging elastic hook is adopted to replace an explosive bolt, so that a separation time sequence test and a separation reliability test can be conveniently carried out, and powerful guarantee is provided for the analysis of the interstage separation performance of the aircraft.
Description
Technical Field
The invention relates to the technical field of aircraft cabin unlocking separation tests, in particular to a test device for researching an aircraft cabin unlocking separation time sequence and separation reliability.
Background
The aerospace craft is composed of a plurality of sub-cabin sections, and separation actions are required to be completed according to a preset time sequence in the flight process. With the continuous improvement of the reliability of each sub-level cabin section of the aircraft, the key for restricting the flight reliability of the whole aircraft becomes the separation action between the sub-level cabin sections.
The separation test device is used for researching and checking the reasonability and reliability of an interstage separation time sequence. The existing aircraft interstage separation test is tested by using an explosion bolt matched with a bomb in a research stage, and the following problems mainly exist:
1) high test cost
The explosive bolts are initiating explosive devices, need use according to national safety management regulations during testing, have special requirements on transportation environment and test places, are high in cost, and especially have high number of explosive bolts required during debugging separation time sequence, so that the test cost is high. And the explosive bolt is a destructive initiating explosive device and inevitably damages the connection part of each sublevel cabin section during testing.
2) The test operation is complicated
Adopt initiating explosive device explosion bolt need have the professional of initiating explosive device operation qualification certificate, and there is the variance in the opening time of explosion bolt, is unfavorable for studying the separation chronogenesis, and explosion bolt is disposable product, restricts experimental study's quantity.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a test device and a method for researching the unlocking separation time sequence and the separation reliability of an aircraft cabin section, and the test device and the method are a non-explosive device ground test device for the separation performance of the aircraft cabin section, can realize the research on the separation time sequence, the separation reliability and the separation attitude, and have simple and reliable structure, and each part can be repeatedly used.
The technical scheme of the invention is as follows:
the test device for researching the unlocking separation time sequence and the separation reliability of the aircraft cabin is characterized in that: comprises a base (1), an electromagnetic hook (2), a locking screw (3) and a latch upright post (5);
the electromagnetic hanging elastic hook (2) is installed on the base (1), the clamp tongue upright post (5) is fixed on the ground, and the cabin A section to be subjected to the separation test is fixed at the lower part of the clamp tongue upright post (5); a spring assembly (6) is arranged between the cabin B section and the cabin A section to be subjected to the separation test, the spring assembly (6) is fixedly connected with the cabin B section, and the spring assembly (6) can be compressed to an initial height position and locked; the upper end of the locking screw rod (3) is fixedly connected with the cabin B section through a nut, and a threaded hole connected with the locking screw rod (3) in the cabin B section is a threaded hole for installing an explosive bolt during the real assembly of the cabin B section; the lower end of the locking screw rod (3) is connected with the electromagnetic hook (2), and the electromagnetic hook (2) can release the lower end of the locking screw rod (3) in a controlled manner;
the upper part of the latch upright post (5) is provided with a spring latch device; the spring latch device comprises a latch (8), a compression spring (9) and a screw (11); the left side and the right side of the position, in which the spring tongue clamping device is arranged, of the tongue clamping upright post (5) are provided with strip-shaped holes in the vertical direction, the spring tongue clamping device is arranged inside the tongue clamping upright post (5), the lower part of the tongue clamping (8) is connected with the tongue clamping upright post (5) through pin shafts (12) arranged in the front and at the back, and the tongue clamping (8) can rotate around the pin shafts (12); one end of the screw rod (11) is fixedly connected with the clamping tongue (8), the other end of the screw rod extends out of the strip-shaped hole on the outer side of the clamping tongue upright post (5), the outer end of the screw rod (11) is provided with a nut (10), the screw rod (11) is sleeved with a compression spring (9), and two ends of the compression spring (9) are restrained by the clamping tongue (8) and the clamping tongue upright post (5);
in an initial state, a compression spring (9) pushes a clamping tongue (8) to be exposed out of a strip-shaped hole in the inner side of a clamping tongue upright post (5), a nut (10) abuts against the clamping tongue upright post (5) for limiting, the upper surface of a structure of the clamping tongue (8) exposed out of the clamping tongue upright post (5) is a plane vertical to the axis of a spring assembly (6), and the lower surface is an inclined plane with an included angle with the upper surface;
when the electromagnetic hanging elastic hook (2) is released, the cabin B section is separated from the cabin A section under the action of the spring assembly (6), the cabin B section can contact the lower surface of the clamping tongue (8) in the separation movement process and pushes the clamping tongue (8) to rotate towards the clamping tongue upright post (5) around the pin shaft (12), then the cabin B section continuously rises and is separated from the clamping tongue (8), the clamping tongue (8) restores to the initial state under the action of the compression spring (9), and when the cabin B section falls behind from the highest point, the cabin B section falls on the upper surface of the clamping tongue (8), and the falling recovery of the cabin B section is completed.
Further preferred scheme, the test device for studying aircraft cabin unlocking separation time sequence and separation reliability is characterized in that: and locking screw rods (3) are arranged at threaded holes of the cabin B section and the cabin A section which are connected by adopting explosive bolts during actual assembly.
The method for researching the unlocking separation time sequence and separation reliability of the aircraft cabin by adopting the test device is characterized by comprising the following steps of: the method comprises a separation time sequence test and a separation reliability test;
the separation timing sequence test comprises the following steps:
step 1: setting the opening time sequence difference of each electromagnetic hanging elastic hook, and controlling each electromagnetic hanging elastic hook to open according to the set time sequence;
step 2: determining the separation attitude change process of the cabin B section under the time sequence of the step 1 through data obtained by a displacement and inertia sensor arranged in the cabin B section and images obtained by high-speed shooting;
and step 3: changing the time sequence set in the step 1, and repeating the step 1 and the step 2 to obtain a plurality of separation attitude change processes of the cabin B section under the time sequence, so as to obtain a separation time sequence meeting the control requirement of the cabin B section;
the separation reliability test refers to that for a planned separation time sequence, a test device is used for repeatedly carrying out a separation test to check the reliability of a separation cabin section.
Advantageous effects
According to the invention, the electromagnetic hanging elastic hook is adopted to replace an explosive bolt, and the non-explosive workpiece ground test device for the interstage separation performance of the aircraft is designed, so that a separation time sequence test and a separation reliability test can be conveniently carried out, and a powerful guarantee is provided for the analysis of the interstage separation performance of the aircraft.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1: a test device (initial installation diagram) for time sequence unlocking ejection separation and recovery;
wherein: 1-a base; 2-electromagnetic hook hanging; 3-locking the screw rod; 4-A cabin section; 5-a latch upright post; 6-a spring assembly; 7-B cabin section;
FIG. 2: a spring latch device; (a) right view (b) front view (initial position) (c) front view (movement position) (d) left view;
wherein: 5-a latch upright post; 8-clamping tongue; 9-a spring; 10-a nut; 11-a screw; 12-a pin shaft;
FIG. 3 is a test apparatus for time-sequential unlocking ejection separation and recovery (bay B bounce);
fig. 4 shows a test apparatus for time-sequential unlocking ejection separation and recovery (B deck recovery).
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
As shown in fig. 1, the test device for researching the unlocking and separating time sequence and the separating reliability of the aircraft cabin section in the embodiment includes a base 1, an electromagnetic hook 2, a locking screw 3, and a latch upright post 5.
The electromagnetic hanging elastic hook 2 is arranged on the base 1, the latch upright post 5 is fixed on the ground, and the section A to be subjected to the separation test is fixed at the lower part of the latch upright post 5; a spring assembly 6 is arranged between the cabin B section and the cabin A section to be subjected to the separation test, the spring assembly 6 is fixedly connected with the cabin B section, and the spring assembly 6 can be compressed to an initial height position and locked; the upper end of the locking screw rod 3 is fixedly connected with the cabin B section through a nut, and a threaded hole connected with the locking screw rod 3 in the cabin B section is a threaded hole for installing an explosive bolt during the actual assembly of the cabin B section; correspondingly, the threaded holes of the cabin B section and the cabin A section which are connected by adopting the explosive bolts during the actual assembly are provided with locking screw rods 3; the lower end of the locking screw rod 3 is connected with the electromagnetic hook 2, and the electromagnetic hook 2 can release the lower end of the locking screw rod 3 in a controlled manner.
As shown in fig. 2, a spring latch device is installed on the upper part of the latch upright post 5; the spring latch device comprises a latch 8, a compression spring 9 and a screw rod 11; the left side and the right side of the position where the spring tongue clamping device is installed in the tongue clamping upright post 5 are provided with strip-shaped holes in the vertical direction, the spring tongue clamping device is installed inside the tongue clamping upright post 5, the lower part of the tongue clamping 8 is connected with the tongue clamping upright post 5 through a pin shaft 12 which is installed in the front and at the back, and the tongue clamping 8 can rotate around the pin shaft 12; one end of the screw rod 11 is fixedly connected with the latch 8, the other end of the screw rod extends out of the strip-shaped hole on the outer side of the latch upright post 5, the outer end of the screw rod 11 is provided with a nut 10, the screw rod 11 is sleeved with a compression spring 9, and two ends of the compression spring 9 are restrained by the latch 8 and the latch upright post 5.
As shown in fig. 3 and 4, in an initial state, the compression spring 9 pushes the latch 8 to be exposed from the strip-shaped hole on the inner side of the latch upright post 5, the nut 10 abuts against the latch upright post 5 for limiting, at this time, the upper surface of the structure of the latch 8 exposed out of the latch upright post 5 is a plane perpendicular to the axis of the spring assembly 6, and the lower surface is an inclined plane having an included angle with the upper surface.
Before the test, the spring of the spring assembly 6 is unlocked, and the spring assembly 6 keeps a compression state under the constraint of the locking screw rod 3; during the test, a control time sequence sends an unlocking instruction to the electromagnetic bullet hanging hook 2, after the electromagnetic bullet hanging hook 2 is released, the locking screw 3 is separated from the electromagnetic bullet hanging hook 2, the cabin B section is separated from the cabin A section under the action of the spring assembly 6, the cabin B section can contact the lower surface of the clamping tongue 8 in the separation movement process and pushes the clamping tongue 8 to rotate around the pin shaft 12 towards the clamping tongue upright post 5, then the cabin B section continuously rises and is separated from the clamping tongue 8, the clamping tongue 8 recovers the initial state under the action of the compression spring 9, and when the cabin B section falls behind from the highest point, the cabin B section falls on the upper surface of the clamping tongue 8 to finish the falling recovery of the cabin B section.
The method for researching the unlocking separation time sequence and the separation reliability of the aircraft cabin section by adopting the test device comprises a separation time sequence test and a separation reliability test.
The separation time sequence test is a test which is carried out by setting the opening time sequences of various electromagnetic hook catches and controlling the opening of each electromagnetic hook catch according to the set time sequences, and in the test process, the separation attitude change process of the cabin B section under the current time sequence is determined through the displacement installed in the cabin B section, data obtained by an inertial sensor and images obtained by high-speed shooting; therefore, the separation attitude change process of the cabin B section under different time sequences is obtained, and the separation time sequence meeting the control requirement of the cabin B section is further obtained.
In addition, the cabin B section and the cabin A section on the real product are connected through 4 explosion bolts, and because errors exist in control precision of the control system and response of the explosion bolts, the maximum response time of the control system and the explosion bolts needed by the aircraft can be analyzed by researching the influence of separation time sequence on the separation attitude; for example, the opening time of 4 hook hooks is respectively set as follows: 1)4 hook hooks are opened simultaneously; 2) and the two groups of the bullet-hanging hooks are in one group, the opening time difference of the two groups of the bullet-hanging hooks is x (ms), the time difference is gradually increased, the maximum time sequence difference capable of meeting the attitude requirement is measured, the maximum response time of a control system and an explosive bolt required by the aircraft can be obtained through the experimental analysis, and the parameter requirement is provided for the subsystems.
The separation reliability test refers to that for a planned separation time sequence, a test device is used for repeatedly carrying out a separation test to check the reliability of the separation cabin section. Because the electromagnetic hook is adopted in the test device, infinite tests are allowed to be carried out theoretically until the test requirements are met.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (3)
1. The utility model provides a test device for studying aircraft cabin unblock separation chronogenesis and separation reliability which characterized in that:
comprises a base (1), an electromagnetic hook (2), a locking screw (3) and a latch upright post (5);
the electromagnetic hanging elastic hook (2) is installed on the base (1), the clamp tongue upright post (5) is fixed on the ground, and the cabin A section to be subjected to the separation test is fixed at the lower part of the clamp tongue upright post (5); a spring assembly (6) is arranged between the cabin B section and the cabin A section to be subjected to the separation test, the spring assembly (6) is fixedly connected with the cabin B section, and the spring assembly (6) can be compressed to an initial height position and locked; the upper end of the locking screw rod (3) is fixedly connected with the cabin B section through a nut, and a threaded hole connected with the locking screw rod (3) in the cabin B section is a threaded hole for installing an explosive bolt during the real assembly of the cabin B section; the lower end of the locking screw rod (3) is connected with the electromagnetic hook (2), and the electromagnetic hook (2) can release the lower end of the locking screw rod (3) in a controlled manner;
the upper part of the latch upright post (5) is provided with a spring latch device; the spring latch device comprises a latch (8), a compression spring (9) and a screw (11); the left side and the right side of the position, in which the spring tongue clamping device is arranged, of the tongue clamping upright post (5) are provided with strip-shaped holes in the vertical direction, the spring tongue clamping device is arranged inside the tongue clamping upright post (5), the lower part of the tongue clamping (8) is connected with the tongue clamping upright post (5) through pin shafts (12) arranged in the front and at the back, and the tongue clamping (8) can rotate around the pin shafts (12); one end of the screw rod (11) is fixedly connected with the clamping tongue (8), the other end of the screw rod extends out of the strip-shaped hole on the outer side of the clamping tongue upright post (5), the outer end of the screw rod (11) is provided with a nut (10), the screw rod (11) is sleeved with a compression spring (9), and two ends of the compression spring (9) are restrained by the clamping tongue (8) and the clamping tongue upright post (5);
in an initial state, a compression spring (9) pushes a clamping tongue (8) to be exposed out of a strip-shaped hole in the inner side of a clamping tongue upright post (5), a nut (10) abuts against the clamping tongue upright post (5) for limiting, the upper surface of a structure of the clamping tongue (8) exposed out of the clamping tongue upright post (5) is a plane vertical to the axis of a spring assembly (6), and the lower surface is an inclined plane with an included angle with the upper surface;
when the electromagnetic hanging elastic hook (2) is released, the cabin B section is separated from the cabin A section under the action of the spring assembly (6), the cabin B section can contact the lower surface of the clamping tongue (8) in the separation movement process and pushes the clamping tongue (8) to rotate towards the clamping tongue upright post (5) around the pin shaft (12), then the cabin B section continuously rises and is separated from the clamping tongue (8), the clamping tongue (8) restores to the initial state under the action of the compression spring (9), and when the cabin B section falls behind from the highest point, the cabin B section falls on the upper surface of the clamping tongue (8), and the falling recovery of the cabin B section is completed.
2. The test device for researching the unlocking separation time sequence and the separation reliability of the aircraft cabin according to claim 1, is characterized in that: and locking screw rods (3) are arranged at threaded holes of the cabin B section and the cabin A section which are connected by adopting explosive bolts during actual assembly.
3. The method for researching the unlocking separation time sequence and the separation reliability of the aircraft cabin by adopting the test device of claim 1 is characterized in that: the method comprises a separation time sequence test and a separation reliability test;
the separation timing sequence test comprises the following steps:
step 1: setting the opening time sequence difference of each electromagnetic hanging elastic hook, and controlling each electromagnetic hanging elastic hook to open according to the set time sequence;
step 2: determining the separation attitude change process of the cabin B section under the time sequence of the step 1 through data obtained by a displacement and inertia sensor arranged in the cabin B section and images obtained by high-speed shooting;
and step 3: changing the time sequence set in the step 1, and repeating the step 1 and the step 2 to obtain a plurality of separation attitude change processes of the cabin B section under the time sequence, so as to obtain a separation time sequence meeting the control requirement of the cabin B section;
the separation reliability test refers to that for a planned separation time sequence, a test device is used for repeatedly carrying out a separation test to check the reliability of a separation cabin section.
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| CN201911209442.6A CN110940531B (en) | 2019-12-01 | 2019-12-01 | Device and method for researching unlocking separation time sequence and reliability of aircraft cabin |
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| CN201911209442.6A CN110940531B (en) | 2019-12-01 | 2019-12-01 | Device and method for researching unlocking separation time sequence and reliability of aircraft cabin |
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| CN110940531B true CN110940531B (en) | 2021-04-13 |
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| CN111483625A (en) * | 2020-04-24 | 2020-08-04 | 北京卫星环境工程研究所 | Device and method for simulating priming of firelock |
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| CN100546876C (en) * | 2007-11-21 | 2009-10-07 | 航天东方红卫星有限公司 | Star or satellite and the rocket separation device |
| CN105486523B (en) * | 2014-10-13 | 2018-03-16 | 北京宇航系统工程研究所 | A kind of mild detonating fuze separator allowance test wire examination method |
| CN104406726B (en) * | 2014-10-31 | 2016-08-31 | 北京宇航系统工程研究所 | A kind of pretightning force and pre-fastening moment device for calibrating relationship between and scaling method |
| CN106338377A (en) * | 2015-08-28 | 2017-01-18 | 中国特种飞行器研究所 | Novel water surface aircraft water load testing device |
| CN106482970B (en) * | 2016-09-30 | 2018-11-06 | 北京强度环境研究所 | A kind of spacecraft Explosive separation guide type safe retrieving experimental rig |
| KR101904197B1 (en) * | 2016-11-02 | 2018-11-21 | 한국항공우주연구원 | Drop testing apparatus and drop testing method of using the same |
| CN106596155A (en) * | 2016-11-18 | 2017-04-26 | 上海宇航系统工程研究所 | Spacecraft separation test system and method |
| CN106568664A (en) * | 2016-11-18 | 2017-04-19 | 上海宇航系统工程研究所 | Spacecraft high/low temperature separation testing system and method |
| CN106706256B (en) * | 2017-02-14 | 2019-01-04 | 中国科学院力学研究所 | A kind of hypersonic aircraft component separation wind tunnel experiment synchronizing exploder |
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