CN114194404A - Throwing recorder and throwing control method thereof - Google Patents
Throwing recorder and throwing control method thereof Download PDFInfo
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- CN114194404A CN114194404A CN202111317756.5A CN202111317756A CN114194404A CN 114194404 A CN114194404 A CN 114194404A CN 202111317756 A CN202111317756 A CN 202111317756A CN 114194404 A CN114194404 A CN 114194404A
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- 238000000926 separation method Methods 0.000 claims abstract description 12
- 238000013500 data storage Methods 0.000 claims description 11
- 238000012544 monitoring process Methods 0.000 claims description 3
- 230000002159 abnormal effect Effects 0.000 abstract description 5
- 206010000369 Accident Diseases 0.000 abstract description 2
- 239000000306 component Substances 0.000 description 23
- 238000010586 diagram Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000001629 suppression Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000005474 detonation Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
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- 239000000463 material Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0065—Black boxes, devices automatically broadcasting distress signals
Abstract
The invention provides a throwing type recorder and a throwing control method thereof, wherein the throwing control method comprises the steps of establishing throwing control conditions according to a safety signal and a plurality of throwing control signals, wherein the throwing control signals comprise a seat pull ring signal, a seat off-position signal, a right main wheel load signal and an inertia contactor signal; receiving a safety signal and a plurality of throwing control signals, and judging the throwing control signals; if the throwing control condition is met, generating a throwing separation signal and starting a positioning starting signal; and if the throwing control condition is not met, not generating a throwing separation signal and not starting a positioning starting signal. The invention also relates to a throwing recorder which comprises a separable component, a throwing control box, an insurance control box, a mounting rack and the like. By designing the throwing control conditions, the throwing of the throwing recorder can be accurately controlled, the separable components are controlled to be thrown after the throwing control conditions are met, the abnormal throwing condition is avoided, and the accurate positioning of the throwing recorder after the aircraft accident is lost is guaranteed.
Description
Technical Field
The invention belongs to the field of avionics, relates to the technology of data recorders, and particularly relates to a throwing recorder and a throwing control method thereof.
Background
The flight accident, namely the flight from taking off before driving to landing after closing the car, the direct threat safety operation that takes place or cause the incident of casualties, aircraft damage or missing, install flight parameter recorder with certain safeguard function on all kinds of aircraft at present to record the various parameters of aircraft in the flight, install throwing the formula recorder on the aircraft simultaneously, when the flight accident appears, can throw out in time the formula recorder of throwing in order to record and keep the aircraft in various flight parameter data in the flight, offer data support for search and rescue and accident analysis etc. in the later stage.
How to determine the throwing condition and throwing time of the throwing recorder plays an important role in the prejudgment and rescue of the search place after the aircraft accident; how to realize that after the throwing type recorder is thrown, the flight parameters can be found in time and extracted to play an important role in analyzing the accident reason.
Disclosure of Invention
The invention aims to design a throwing recorder and a throwing control method thereof, wherein the design of throwing control conditions in the throwing recorder and the throwing control method thereof plays an important role in timely throwing the throwing recorder under any conditions, and the condition that the throwing recorder is abnormally thrown can be avoided. Through the improved design of the throwing recorder, the power supply can be turned on in time to supply electric energy for the separable component when a throwing control signal is received.
The technical scheme for realizing the purpose of the invention is as follows:
in a first aspect, the present invention provides a method for controlling the throwing of a throwing recorder, comprising the following steps:
s1, establishing a throwing control condition according to the safety signal and a plurality of throwing control signals, wherein the throwing control signals comprise a seat pull ring signal, a seat off-position signal, a right main wheel load signal and an inertia contactor signal;
the throwing control conditions include:
when the seat pull ring signal is effective, judging a seat off-position signal, a safety signal and a right main wheel-mounted signal, and if the seat off-position signal is effective, the safety signal is effective and the right main wheel-mounted signal is ineffective, judging that the throwing recorder needs to be thrown out and generating a throwing control signal;
or judging the safety signal and the right main gear signal when the inertial contactor signal is valid, and judging that the throw-type recorder needs to be thrown and generating a throw control signal when the safety signal is valid and the right main gear signal is invalid;
s2, receiving a safety signal and a plurality of throwing control signals, and judging the throwing control signals;
s201, if the throwing control condition is met, generating a throwing separation signal, and starting a positioning starting signal;
s202, if the throwing control condition is not met, no throwing separation signal is generated, and no positioning starting signal is started.
By designing the throwing control conditions of the throwing recorder, the throwing of the throwing recorder can be accurately controlled, so that the throwing control signals are output and the positioning starting signals are started after the throwing recorder reaches the conditions, the abnormal throwing of the throwing recorder is avoided, and the accurate positioning of the throwing recorder after the airplane loses events is guaranteed.
Further, an insurance signal is generated by an insurance control box in the throwing recorder;
if the safety control box is inserted into the safety pin, the safety signal is invalid;
if the safety control box is not inserted into the safety pin, the safety signal is valid.
In a second aspect, the present invention provides a throw-away recorder that executes the throw-away control conditions of the throw-away control method of the first aspect. The throwing recorder comprises a separable assembly, the separable assembly is detachably mounted on the mounting frame, and a positioning module, a data storage module and a power supply module are arranged in the separable assembly.
The input end of the separable component is connected with a throwing control box, and a data receiving module and a signal receiving module are arranged in the throwing control box.
The output end of the data receiving module is connected with the flight parameter acquisition equipment, the output end of the data receiving module is connected with the data storage module of the separable component, and the data receiving module is used for receiving the flight parameter data and sending the flight parameter data to the data storage module for storage.
The input end of the signal receiving module is connected with the aircraft seat system, the undercarriage system and the inertial contactor and is used for receiving the throwing control signals output by the aircraft seat system, the undercarriage system and the inertial contactor.
The output end of the signal receiving module is connected with a judging module, the judging module receives the throwing control signal, judges whether the throwing control condition is met or not according to the throwing control logic, generates a throwing separation signal if the throwing control condition is met, and starts a positioning starting signal.
Furthermore, the throwing control box also comprises a self-checking module, wherein the self-checking module is connected with the data receiving module, the signal receiving module and the judging module and is used for detecting the data receiving module, the signal receiving module and the judging module.
Furthermore, the throwing control box also comprises an alarm module, and the alarm module is connected with the power supply module in the separable component and is used for monitoring the electric energy stored in the power supply module.
Further, the throwing control signal includes a seat off-position signal and a seat pull ring signal output by the aircraft seat system, a right main wheel-mounted signal output by the landing gear system, and an inertia contactor signal output by the inertia contactor.
Furthermore, the throwing recorder also comprises a safety control box assembly, the safety control box assembly comprises a safety control box and a safety bolt, the safety control box is connected with the judgment module, and the safety control box is used for outputting a safety signal to the judgment module.
Furthermore, a flash frequency lamp module is also arranged on the separable component.
In a third aspect, the invention provides a flight parameter recording system, which comprises the jettisoning recorder of the second aspect, and jettisoning control conditions for executing the jettisoning control method of the first aspect.
The flight parameter recording system also comprises a flight parameter collector, a flight parameter recorder and a quick access recorder which are connected with the throwing control box.
Further, the flight parameter collector is connected with the throwing control box through an HDLC bus.
Compared with the prior art, the invention has the beneficial effects that:
1. by designing the throwing control conditions of the throwing recorder, the throwing of the throwing recorder can be accurately controlled, so that the throwing control signals are output and the positioning starting signals are started after the throwing recorder reaches the set conditions, the abnormal throwing of the throwing recorder is avoided, and the accurate positioning of the throwing recorder after the airplane loses events is guaranteed.
2. The throwing type recorder is improved, so that a signal receiving module is arranged in a throwing control box and used for receiving throwing control signals from an airplane, meanwhile, the judging module is designed to judge the received throwing control signals and then generate throwing separation signals and starting positioning starting signals, and the separable components are thrown and start a positioning working mode. Through the design of the warning module, the power supply module in the separable component is monitored in real time in the normal flight of the airplane, and the electric energy of the power supply module is ensured.
Drawings
In order to more clearly illustrate the technical solution of the embodiment of the present invention, the drawings used in the description of the embodiment will be briefly introduced below. It should be apparent that the drawings in the following description are only for illustrating the embodiments of the present invention or technical solutions in the prior art more clearly, and that other drawings can be obtained by those skilled in the art without any inventive work.
FIG. 1 is a flow chart of a method for controlling the ejection of a drop recorder in accordance with an embodiment of the present invention;
FIG. 2 is a block diagram of a throw-recorder in accordance with an embodiment of the present invention;
FIG. 3 is a schematic diagram illustrating the connection of the components of the flight parameter recording system in accordance with an embodiment of the present invention;
wherein, 2, the assembly can be separated; 3. throwing the control box; 4. a fuse control box assembly; 201. a positioning module; 202. a data storage module; 203. a power supply module; 204. a strobe light module; 301. a data receiving module; 302. a signal receiving module; 303. a judgment module; 304. a self-checking module; 305. and an alarm module.
Detailed Description
The invention will be further described with reference to specific embodiments, and the advantages and features of the invention will become apparent as the description proceeds. These examples are illustrative only and do not limit the scope of the present invention in any way. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention, and that such changes and modifications may be made without departing from the spirit and scope of the invention.
In the description of the present embodiments, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
The specific embodiment designs a throwing control method of a throwing recorder, and as shown in fig. 1, the throwing control method includes the following steps:
s1, establishing a throwing control condition according to the safety signal and a plurality of throwing control signals, wherein the throwing control signals comprise a seat pull ring signal, a seat off-position signal, a right main wheel load signal and an inertia contactor signal;
the throwing control conditions include:
a. when the seat pull ring signal is effective, judging a seat off-position signal, a safety signal and a right main wheel-mounted signal, and if the seat off-position signal is effective, the safety signal is effective and the right main wheel-mounted signal is ineffective, judging that the throwing recorder needs to be thrown out and generating a throwing control signal;
and b, judging the safety signal and the right main wheel-mounted signal when the inertial contactor signal is effective, and judging that the throwing recorder needs to be thrown out and generating a throwing control signal when the safety signal is effective and the right main wheel-mounted signal is invalid.
In the step, a seat pull ring signal and a seat off-position signal are output by an airplane seat system on an airplane seat; the right main wheel-borne signal is output by an undercarriage system on an undercarriage; the inertial contactor signal (i.e., the crash signal) is output by the inertial contactor.
In this step, the insurance signal is generated by an insurance control box in the throw-type recorder. If the safety control box is inserted into the safety pin, the safety control box is disconnected from the throwing recorder, and the safety control box does not output a safety signal to the throwing recorder, so that the safety signal is invalid; if the safety control box is not inserted with the safety pin, the safety control box is connected with the throwing recorder, and the safety control box does not output a safety signal to the throwing recorder, so that the safety signal is effective.
S2, receiving a safety signal and a plurality of throwing control signals, and judging the throwing control signals;
s201, if the throwing control condition is met, a throwing separation signal is generated, and a positioning starting signal is started.
In this step, when either of the conditions a or b is satisfied, it is determined that the throw-away recorder needs to be thrown away, at this time, a throw-away control signal is generated to throw away the separable component of the throw-away control box, and a start positioning start signal is sent to the separable component, so that the separable component starts positioning.
S202, if the throwing control condition is not met, no throwing separation signal is generated, and no positioning starting signal is started.
In this step, when either a or b is not satisfied, it is determined that the throw-away recorder does not need to be thrown away, and at this time, no throw-away control signal is generated and no positioning start signal is started.
By designing the throwing control conditions of the throwing recorder, the throwing of the throwing recorder can be accurately controlled, so that the throwing control signals are output and the positioning starting signals are started after the throwing recorder reaches the set conditions, the abnormal throwing of the throwing recorder is avoided, and the accurate positioning of the throwing recorder after the airplane loses events is guaranteed.
The specific embodiment further designs a throw-away recorder, and fig. 2 shows a structural block diagram of the throw-away recorder.
The throw-type recorder includes a separable assembly 2, and the separable assembly 2 is detachably mounted on a mounting bracket. In this embodiment, the mounting bracket is used to fix the separable component 2, and may be fixed to the aircraft through the flanged mounting hole, or may adopt other fixing methods, and the material of the mounting bracket may be arbitrarily selected, which is not limited herein.
As shown in fig. 2, a positioning module 201, a data storage module 202, and a power supply module 203 are disposed in the separable component 2.
Specifically, the positioning module 201 is used for positioning the separable component 2 after the separable component 2 is ejected. In this embodiment, the positioning module 201 selects the beidou beacon module preferentially, which has the receiving function of RNSS and RDSS-S frequency points and the transmitting function of RDSS-L frequency points, so that the separable component 2 can be searched according to the beidou positioning signal after being thrown and separated, and the positioning accuracy can be accurate to 20 m.
The data storage module 202 is used for receiving and storing various flight parameter data acquired by the flight parameter acquisition equipment on the airplane.
Power module 203 is used to provide power to the various modules within separable assembly 2 after separable assembly 2 is ejected, determining the proper operation of the various modules within separable assembly 2.
As an improvement to the separable assembly 2, as shown in fig. 2, a strobe light module 204 is further provided on the separable assembly 2, and the strobe light module 204 is activated after the separable assembly 2 is ejected.
As shown in fig. 2, the input end of the separable component 2 is connected with a throwing control box 3, the throwing control box 3 is one of the core components of the throwing recorder, on one hand, a 28V dc power supply is converted into a 12V power supply and an internal required power supply after being filtered, and peak voltage suppression, surge voltage suppression and energy storage functions are provided; on the other hand, a data receiving module 301, a signal receiving module 302, a judging module 303 and a self-checking module 304 are arranged in the throwing control box 3, and whether the separable component 2 needs to be thrown or not is accurately judged through mutual cooperation among the modules.
Specifically, as shown in fig. 2, an output end of the data receiving module 301 is connected to the flight parameter collecting device, an output end of the data receiving module is connected to the data storage module 202 of the separable component 2, and the data receiving module 202 is configured to receive the flight parameter data and send the flight parameter data to the data storage module 202 for storage.
As shown in fig. 2, an input end of the signal receiving module 302 is connected to the aircraft seat system, the landing gear system, and the inertial contactor, and is configured to receive the launch control signal output by the aircraft seat system, the landing gear system, and the inertial contactor.
As shown in fig. 2, the output end of the signal receiving module 302 is connected to a judging module 303, the judging module 303 receives the throwing control signal, judges whether the throwing control condition is met according to the throwing control method, generates a throwing separation signal if the throwing control condition is met, and starts a positioning start signal.
In a preferred embodiment of the foregoing discharge control box, as shown in fig. 2, the discharge control box 3 further includes a self-checking module 304, where the self-checking module 304 is connected to the data receiving module 301, the signal receiving module 302, and the judging module 303, and detects the data receiving module 301, the signal receiving module 302, and the judging module 303, and the self-checking module 304 monitors each module in the discharge control box 3 in real time to ensure that each module is in a normal working state.
In a preferred embodiment of the above-mentioned discharge control box, as shown in fig. 2, the discharge control box 3 further comprises an alarm module 305, and the alarm module 305 is connected to the power supply module 203 in the detachable component 2 for monitoring the power stored in the power supply module 203.
Specifically, the throwing control signal received by the signal receiving module 302 includes a seat off-position signal and a seat pull ring signal output by the aircraft seat system, a right main wheel load signal output by the landing gear system, and an inertia contactor signal output by the inertia contactor.
In a preferred embodiment of the above-mentioned jettisoning recorder, as shown in fig. 2, the jettisoning recorder further includes a safety control box assembly 4, where the safety control box assembly 4 includes a safety control box and a safety plug, the safety control box is connected to the judging module 303, and the safety control box is configured to output a safety signal to the judging module 303. In this embodiment, the safety control box assembly 4 is composed of two micro switches and a driving system, and the driving system includes a safety bolt, a limiting groove, and a spring plate. When the safety bolt is inserted into the safety control box, the safety bolt pushes the elastic sheet in the limit groove, so that the elastic sheet presses the micro switch, and the safety control box is disconnected from the judgment module 303 after the micro switch acts, so that the current is prevented from flowing.
Through the arrangement of the safety control box assembly 4, the risk of abnormal throwing of 2 times of the separable assembly caused by misoperation can be avoided, for example, when an airplane is parked or overhauled on the ground, if the safety control box is not disconnected from the judgment module 303, a safety signal is possibly output to the judgment module 303, so that the judgment module 303 makes an erroneous judgment. After the safety bolt is inserted into the safety control box, the safety control box can be disconnected with the judgment module 303, the judgment module 303 cannot receive a safety signal, the condition that the judgment module 303 judges by mistake can be avoided, the accidental detonation is prevented, and the safety function is achieved.
The specific embodiment further provides a flight parameter recording system, wherein the flight parameter recording system comprises the throwing type recorder and throwing control conditions for executing the throwing control method.
The flight parameter recording system comprises a flight parameter collector, a flight parameter recorder and a quick access recorder which are connected with the throwing control box besides an inertia contactor, an undercarriage system and an airplane seat system. The connection mode and signal transmission between each component of the flight parameter recording system and the throwing control box are shown in fig. 3, and in the real-time mode, the flight parameter collector and the throwing control box are preferentially connected through an HDLC bus, and during design, an HDLC high-level data link of a main computer module is added in the flight parameter collector and connected with the throwing control box through the HDLC bus, so that the data transmission of the flight parameter collector is met and ensured.
In this embodiment, the throw of the separable assembly 2 of the throw control box is in the following forms: the separable component 2 is thrown in disaster events such as the collision of the airplane on the ground or water surface, the collision in the air or the explosion, and the like, and records the last data before the airplane crashes as much as possible; the separable component 2 is not thrown in non-catastrophic events such as hard landing, tail strike, normal service; the two throwing modes are judged according to the throwing control conditions of the throwing control method.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (10)
1. A throwing control method of a throwing recorder is characterized by comprising the following steps:
s1, establishing a throwing control condition according to the safety signal and a plurality of throwing control signals, wherein the throwing control signals comprise a seat pull ring signal, a seat off-position signal, a right main wheel load signal and an inertia contactor signal;
the throwing control conditions comprise:
when the seat pull ring signal is effective, judging a seat off-position signal, a safety signal and a right main wheel-mounted signal, and if the seat off-position signal is effective, the safety signal is effective and the right main wheel-mounted signal is ineffective, judging that the throwing recorder needs to be thrown out and generating a throwing control signal;
or judging the safety signal and the right main gear signal when the inertial contactor signal is valid, and judging that the throw-type recorder needs to be thrown and generating a throw control signal when the safety signal is valid and the right main gear signal is invalid;
s2, receiving a safety signal and a plurality of throwing control signals, and judging the throwing control signals;
s201, if the throwing control condition is met, generating a throwing separation signal, and starting a positioning starting signal;
s202, if the throwing control condition is not met, no throwing separation signal is generated, and no positioning starting signal is started.
2. The discharge control method according to claim 1, characterized in that: the safety signal is generated by a safety control box in the throwing recorder;
if the safety control box is inserted into the safety pin, the safety signal is invalid;
if the safety control box is not inserted into the safety pin, the safety signal is valid.
3. A throw-type recorder which executes a throw control condition of the throw control method according to claim 1 or 2, characterized in that: the throwing recorder comprises a separable assembly, the separable assembly is detachably mounted on the mounting frame, and a positioning module, a data storage module and a power supply module are arranged in the separable assembly;
the input end of the separable component is connected with a throwing control box, and a data receiving module and a signal receiving module are arranged in the throwing control box;
the output end of the data receiving module is connected with flight parameter acquisition equipment, the output end of the data receiving module is connected with the data storage module of the separable component, and the data receiving module is used for receiving flight parameter data and sending the flight parameter data to the data storage module for storage;
the input end of the signal receiving module is connected with the aircraft seat system, the undercarriage system and the inertial contactor and is used for receiving the throwing control signals output by the aircraft seat system, the undercarriage system and the inertial contactor;
the output end of the signal receiving module is connected with a judging module, the judging module receives the throwing control signal, judges whether the throwing control condition is met or not according to the throwing control logic, generates a throwing separation signal if the throwing control condition is met, and starts a positioning starting signal.
4. A throw recorder according to claim 3, wherein: the throwing control box further comprises a self-checking module, wherein the self-checking module is connected with the data receiving module, the signal receiving module and the judging module and is used for detecting the data receiving module, the signal receiving module and the judging module.
5. A throw recorder according to claim 3, wherein: the throwing control box further comprises an alarm module, and the alarm module is connected with the power supply module in the separable assembly and is used for monitoring the electric energy stored in the power supply module.
6. A jettisoning recorder according to any one of claims 3 to 5, wherein: the throwing control signal comprises a seat off-position signal and a seat pull ring signal output by the aircraft seat system, a right main wheel-mounted signal output by the undercarriage system and an inertia contactor signal output by the inertia contactor.
7. A jettisoning recorder according to any one of claims 3 to 5, wherein: the throwing recorder further comprises a safety control box assembly, the safety control box assembly comprises a safety control box and a safety bolt, the safety control box is connected with the judging module, and the safety control box is used for outputting a safety signal to the judging module.
8. A jettisoning recorder according to any one of claims 3 to 5, wherein: and a flash frequency lamp module is also arranged on the separable component.
9. A flight parameter recording system, comprising the jettisoning recorder of any one of claims 3 to 8, and jettisoning control conditions for performing the jettisoning control method of claim 1 or 2;
the flight parameter recording system also comprises a flight parameter collector, a flight parameter recorder and a quick access recorder which are connected with the throwing control box.
10. A flight parameter recording system according to claim 9, wherein: the flight parameter collector is connected with the throwing control box through an HDLC bus.
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| CN202111317756.5A CN114194404A (en) | 2021-11-08 | 2021-11-08 | Throwing recorder and throwing control method thereof |
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Cited By (1)
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| CN114537668A (en) * | 2022-04-26 | 2022-05-27 | 成都凯天电子股份有限公司 | Locking and ejecting mechanism of throwing type flight parameter recorder and control method thereof |
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| CN112874795A (en) * | 2021-01-21 | 2021-06-01 | 北京京东乾石科技有限公司 | Throwing device, unmanned aerial vehicle, control method, control device and storage medium |
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| CN114537668A (en) * | 2022-04-26 | 2022-05-27 | 成都凯天电子股份有限公司 | Locking and ejecting mechanism of throwing type flight parameter recorder and control method thereof |
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